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EP2818635A1 - Drum of axial turbomachine compressor with mixed fixation of blades - Google Patents

Drum of axial turbomachine compressor with mixed fixation of blades Download PDF

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Publication number
EP2818635A1
EP2818635A1 EP13173510.2A EP13173510A EP2818635A1 EP 2818635 A1 EP2818635 A1 EP 2818635A1 EP 13173510 A EP13173510 A EP 13173510A EP 2818635 A1 EP2818635 A1 EP 2818635A1
Authority
EP
European Patent Office
Prior art keywords
row
blades
drum
rotor
wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13173510.2A
Other languages
German (de)
French (fr)
Other versions
EP2818635B1 (en
Inventor
Enrique Penalver Castro
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP13173510.2A priority Critical patent/EP2818635B1/en
Priority to CA2853663A priority patent/CA2853663A1/en
Priority to RU2014125101/02A priority patent/RU2576354C2/en
Priority to US14/315,097 priority patent/US20140377070A1/en
Priority to CN201410290159.1A priority patent/CN104251232B/en
Publication of EP2818635A1 publication Critical patent/EP2818635A1/en
Application granted granted Critical
Publication of EP2818635B1 publication Critical patent/EP2818635B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/063—Welded rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings

Definitions

  • the invention relates to a turbomachine rotor. More specifically, the invention relates to an axial turbomachine compressor rotor drum. The invention relates to an axial turbomachine with a low pressure compressor rotor drum.
  • a turbomachine makes it possible to subject a gas to compression, combustion and relaxation.
  • the turbomachine thereby provides mechanical energy.
  • the turbomachine comprises a compressor and a turbine which are provided with a rotor and a housing.
  • the inner surface of the housing and the outer surface of the rotor outline the contours of the primary vein. This presents variations of annular sections. Its inner and outer contours can increase and decrease in diameter along the axis of the turbomachine.
  • the outer casing At the level of a compressor, particularly of the low-pressure type, the outer casing generally has a decrease in diameter downstream. From upstream to downstream, the rotor may have an increase in diameter, and then a reduction in diameter. This combination of surfaces makes it possible to have an extended input and to reach a high compression ratio at the output.
  • the compressor housing and rotor each comprise several annular rows of blades.
  • the rows of rotor blades and rows of stator vanes axially form an alternation.
  • the housing may comprise a plurality of annular rectifiers which each comprise an annular array of blades. Rectifiers form rings that are axially reported against each other for attachment. In this case, each blade of the rotor rows is fixed to the rotor via a foot introduced into an annular groove formed on the rotor.
  • a first row of blades is mounted on the rotor, and an annular rectifier is axially attached facing this first row. Then only, a second blade row succeeding the rectifier with respect to the first row can be mounted on the rotor. The assembly continues so on, rising in turn a row of rotor blades and a rectifier. This method of assembly is imposed by the monobloc aspect of the rectifiers and their internal diameters which do not allow to introduce the rotor with its blades.
  • the document FR 2 845 436 B1 discloses an axial turbomachine compressor.
  • the compressor comprises an outer casing formed of several rectifiers axially reported. It also includes annular rows of blades which are each placed between the rectifiers. The blades of the rotor are fixed with feet which are inserted into annular grooves formed in the rotor.
  • This embodiment makes it possible to produce a simple compressor to be assembled.
  • the rotor is subjected to vibrations. It develops complex vibration modes that are difficult to analyze and dampen.
  • its realization requires complex and expensive machining. Add to that that its architecture remains massive and heavy.
  • the invention aims to solve at least one of the problems raised by the state of the art. More specifically, the invention aims to reduce the vibrations of a rotor of an axial turbomachine. The invention also aims to lighten an axial turbomachine rotor.
  • the subject of the invention is an axial turbomachine rotor drum, in particular a low-pressure compressor, the drum comprising a wall that is generally symmetrical in revolution about its axis and having a curved general profile, said wall being configured to support several rows of tubes. blades; remarkable in that a first row of blades is formed by an annular platform integrally formed with the wall at the top of its profile relative to the axis; and at least one, preferably each, of a second row of blades directly downstream of the first and third rows of blades directly upstream of the first, is formed by one or more blade retention grooves, formed on the wall.
  • the outer surface of the retention groove or grooves is at an average distance from the axis which is less than the average distance from the platform of the first row to said axis.
  • the wall comprises on its outer surface a set of annular ribs adapted to cooperate with an annular layer of abradable material so as to ensure a seal, the rib play being arranged axially between the first and second rows of blades and / or between the first and third rows of blades.
  • the minimum distance of the vertices of one of the sets of ribs with respect to the axis is greater than the maximum distance with respect to said axis of the outer surface of the adjacent retention groove or grooves. This is the groove or throats of the second and / or third row (s) of blades.
  • the blades of the first row are welded to the platform of said row.
  • the platform of the first row of blades comprises blade stubs on which blade extensions are welded, preferentially blade stubs represent more than 10% of the radial height of the blades. blades of the first row, more preferably more than 25%.
  • the blades of the first row are at least partially cut in the mass of a raw drum.
  • the curved general profile of the wall extends over most of the length of the drum and / or has a main concavity directed towards the axis and extending over most of the length of the drum. length of the drum, said profile having a radius, with respect to the axis, which is maximum at the first row of blades.
  • the platform of the first row of blades is raised relative to the wall directly upstream and downstream of said row.
  • the wall comprises two portions extending generally radially under the platform of the first row, so that the longitudinal section of the wall at said platform has a profile in the form of ⁇ . .
  • the wall comprises at least one annular stiffener extending radially inwards at the first row of blades, preferably in the extension of at least one of the radial portions.
  • the wall directly upstream and downstream of the first row comprises a portion of substantially constant thickness which delimits an annular space intended to receive a rectifier inner shell.
  • the rotor drum comprises the blades of the second and / or third row of blades, each of said blades comprising a foot housed in the or one of the retention grooves.
  • the retention groove or grooves are annular along the perimeter of the drum.
  • the blades of the first row and the annular platform form a one-piece assembly.
  • the drum is made of metallic material, preferably titanium.
  • the wall is forged and cut into the mass.
  • the annular platform and the retention grooves are integral.
  • the drum shows a continuity of material between the blades of the first row and the wall.
  • a set of annular ribs is distributed axially on the annular junction.
  • all rows of blades of the drum, except the first, comprise a blade retention groove for assembly on the drum.
  • the invention also relates to an axial turbomachine comprising a rotor drum, remarkable in that the drum is in accordance with the invention, preferably the rotor is a low-pressure compressor rotor comprising essentially three annular rows of rotor blades.
  • the invention makes it possible to reduce the vibrations of an axial turbomachine rotor. For this it removes the freedom of movement between the annular wall and the blades of the first row.
  • the invention improves the overall rigidity of the drum.
  • the proposed architecture also makes it possible to lighten the rotor, by acting on both the drum and the blades.
  • the invention is applied to a drum provided with annular ribs as a sealing means between the compression stages.
  • This aspect is not limiting since the invention can also be applied to a drum cooperating with axial brush seals.
  • Such seals are well known to those skilled in the art and may, for example, correspond to those disclosed in the document DE102005042272 A1 .
  • the figure 1 represents an axial turbomachine according to the invention.
  • the figure 2 is a diagram of a turbomachine compressor according to the invention.
  • the figure 3 illustrates a section of the rotor drum according to the invention.
  • inner or inner and outer or outer refer to a positioning relative to the axis of rotation of the axial turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • Reducing means can increase the speed of rotation transmitted to the compressors.
  • the different turbine stages can each be connected to the compressor stages via concentric shafts.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 10.
  • a commonly designated fan inlet fan 16 is coupled to the rotor 12 and generates a flow of air which is divided into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow out of turbine.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical walls or ferrules which can be internal and external.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine 2 such as that of the figure 1 .
  • the compressor may be a low pressure compressor 4.
  • the teaching of the present invention may also be applied to a turbine rotor drum 10.
  • the rotor 12 comprises several annular rows of rotor blades, in the specific case of the figure 2 three rows are planned. More rows of vanes can be provided. These three rows are axially successive. A first row of rotor blades 24, a second row of rotor blades 26 downstream of the first row 24 and a third row of rotor blades 28 upstream of the first row 24 are observed.
  • the rotor blades (24, 26, 28) extend substantially radially from the rotor 12.
  • the blades of the same row are regularly spaced from each other, and have the same angular orientation in the flow.
  • the spacing between the vanes may vary locally, as can their angular orientation. Some blades may be different from the rest of the blades of the corresponding row.
  • the compressor 4 comprises an outer casing.
  • the outer casing comprises a plurality of rectifiers, for example four, which each comprise an outer shell 30, a row of stator vanes 32 and optionally an inner shell 34.
  • An annular layer of abradable material 36 may be applied inside the shell.
  • the stator vanes 32 of the same rectifier extend radially from their outer shell 30 to their inner shell 34.
  • the rectifiers form circularly closed rings. They are reported axially against each other and fixed to each other by means of radial flanges 38.
  • the rectifiers are associated with the fan or a row of rotor vanes (24, 26, 28) for straightening the airflow, so as to convert the speed of the flow into pressure.
  • the rotor 12 comprises a drum 40.
  • the drum 40 comprises a wall 42 generally symmetrical in revolution about its axis of rotation 14, which axis is common with that of the turbomachine.
  • the wall 42 may have a general profile of revolution or average profile of revolution about the axis of rotation 14. The general profile may be included in the thickness of the portions of the wall 42 which are axially right rows of vanes stator.
  • the overall profile is essentially curved and may have a continuous curvature and / or a continuous curvature variation. It follows radially the section variation of the inner surface of the primary stream 18.
  • the outside of the general profile is convex. From upstream to downstream, the radius of the inner surface increases and then decreases, so that the profile of the wall has a peak.
  • the wall 42 is essentially thin. Its thickness is generally constant. Its thickness is less than 10.00 mm, preferably less than 5.00 mm, more preferably less than 2.00 mm.
  • the wall 42 forms a hollow body which delimits a hollow space, having an ogive or barrel shape.
  • the drum 40 and / or the rotor blades (24, 26, 28) are made of metallic materials, preferably of titanium.
  • the drum 40 comprises annular ribs 44 or wipers. They form annular lamellae which extend radially. They are intended to cooperate by abrasion with annular layers of abradable material 36 of a rectifier so as to ensure a seal. Generally, one and the same abradable layer 36 cooperates with two annular ribs 44.
  • the figure 3 is detail view in section of the drum 40 of the figure 2 .
  • the drum may also be a high pressure compressor rotor drum. It may possibly be a turbine rotor drum.
  • the first row of vanes 24 is formed on the wall by an annular platform 46.
  • the annular platform 46 is integrally formed with the wall 42.
  • the annular platform 46 is formed at the top of the profile of the wall 42.
  • the annular platform 46 has a generally straight or substantially curved profile of revolution.
  • the rotor blades of the second row 26 and the third row 28 each comprise a blade platform 48 defining the inside of the primary flow, a blade 50 extending radially outwardly from the blade platform 46, and a retention foot 52 extending radially inwardly from the blade platform 48.
  • the retention foot 52 may have a dovetail shape. It may have a shape whose axial dimension increases when one gets closer to the interior, so as to allow commitment of material.
  • the wall 42 of the drum 40 comprises two blade attachment zones by retention groove.
  • the fixing zones each comprise an annular groove 54 into which the retention feet 52 of the blades of the second row 26 and of the third row 28 are introduced.
  • the annular grooves 54 comprise annular outer surfaces against which the platforms of 48.
  • the blade platforms 48 of the second row of blades 26 come into contact with the second outer surface 56, and the blade platforms 48 the third row of blades 28 come into contact with the third outer surface. 58.
  • the retention feet 52 generally have a shape complementary to the corresponding retention groove, so as to ensure radial retention.
  • the retention grooves 54 have a profile with a narrowing at their outlet, to the outside.
  • a mechanical clearance is provided between the annular wall 42 and the rotor blades of the second and third rows, so as to allow a slight movement of the blades.
  • the rotor is configured so that the centrifugal force present during operation of the plate compressor in position the blades in their groove.
  • the retention grooves may be axial grooves.
  • the annular wall then comprises an annular row of axial grooves distributed over its circumference, and which each form an annular row of vanes.
  • the outer surface (56, 58) of at least one of the annular grooves 48 is at an average distance from the axis 14 which is less than the average distance from the annular platform 46 of the first row 24 of said axis.
  • each radius of an axial end of the annular platform 46 is greater than the maximum radius of the outer surface (56, 58) disposed opposite.
  • the blades of the first row 24 are anchored to the drum in a different fashion from the other rows (26; 28).
  • the retention or fixation of the blades is heterogeneous or hybrid.
  • the blades of the first row 24 are fixed by welding on the annular platform 46. They can be friction welded, for example by an orbital welding process.
  • the drum 40 thus serves as a support for fixing two types of blades.
  • blades corresponding to the first row 24 are attached to a raw drum and welded to the annular platform 46. These vanes can be directly or indirectly attached to the annular platform 46.
  • the annular platform 46 may include stubs. blades 60 which extend radially from its outer surface. In this case, each blade which is welded to the second surface actually forms only a radial portion of the final blade.
  • the weld 62 between a stump and a blade portion is in elevation relative to the annular platform 46.
  • the blades of the first row 24 can be integrally machined in the mass of a raw drum in which the wall is also machined.
  • the wall of the drum 40 and the blades 24 of the first row form a one-piece assembly. They present a continuity of matter. Their metallic materials have a crystalline continuity at their interface. They can be at least partially come from matter. The anchoring of the vanes is irreversible.
  • the blades of the first row 24 are integral with the annular wall 42. This embodiment makes it possible to eliminate vibrations between the blades of the first row 26 and the wall 42 of the drum 40.
  • this method of anchoring the blades simplifies the machining to be performed because the annular platform 46 and any stubs 60 are simpler to achieve than an annular groove or several axial grooves. Indeed, a groove must be cut in a generally inaccessible space with a small tool, which lengthens the manufacturing time. Or, an axial groove can be machined by broaching. However, this material removal process requires expensive tooling and is not compatible with all drum shapes.
  • the wall 42 of the drum directly upstream and downstream of the first row of blades 24 comprises at least one portion of substantially constant thickness 64 or axial annular junction 64, preferably two portions of essentially constant thicknesses 64.
  • Each portion of constant thickness 64 extends axially from the annular platform 46 to the second row of blades 26 or to the third row of blades 28.
  • the annular platform 46 is radially in annular elevation with respect to each portion of constant thickness 64.
  • the portions of constant thicknesses 64 define an annular space between the first row of blades 26 and the second row of blades 28 or the third row of blades 24, these annular spaces being open radially outwardly. They are intended to house internal ferrules of rectifiers.
  • the wall 42 comprises two portions 65 which extend generally radially. They extend from the annular platform 46 inwards. They may each be arranged at one of the axial edges of the annular platform 46. In this way, the wall may have a profile of the general Greek letter ⁇ .
  • the profiles of the radial portions extend generally perpendicular to the profile of the annular platform 46.
  • the annular ribs 44 are arranged on the portions of constant thicknesses 64. Each rib set comprises several ribs 44. On each side of the annular platform 46 there is a decrease progressive outer rays from an edge of the annular platform 46, ribs 44, and outer surfaces (56; 58) of the annular grooves. The tops of these elements form a staircase. This configuration makes it possible to report bladed rectifiers on either side of the first row of blades 24, then to assemble the second row 26 and the third row 28.
  • the figure 3 illustrates the blades 32 and the inner shroud 36 of the two rectifiers upstream and downstream, respectively, of the first row of blades 24.
  • the figure 3 also shows in broken lines these rectifiers in an intermediate position of assembly, in an axial direction, around the drum.
  • the annular wall 42 of the drum includes annular stiffeners 66.
  • the annular stiffeners 66 may include annular flanges that extend radially inwardly. These flanges are arranged axially at the ends of the annular platform 46, preferably in the radial extension of the radial portions 65.
  • the drum is generally machined by turning from a drum-shaped machining blank whose walls encompass the finished drum.
  • the raw drum must radially encompass the outer surfaces of the annular grooves 54, the annular platform 46, the internal stiffeners 66, and any blade stubs 60. As the case may be, it may encompass the blades of the first row 54 over their entire length. radial height.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention a trait à un tambour rotorique (40) de compresseur basse-pression de turbomachine axiale. Le tambour (40) comprend une paroi (42) généralement symétrique en révolution autour de son axe (14) et suivant un profil général courbé. La paroi (42) est configurée pour supporter plusieurs rangées d'aubes (24 ; 26 ; 28). Une première rangée d'aubes (24) est formée par une plateforme annulaire (46) intégralement formée avec la paroi (42), au sommet de son profil par rapport à l'axe (14) ; et d'une deuxième rangée d'aubes (26) directement en aval de la première (24) et d'une troisième rangée d'aubes (28) directement en amont de la première (24), sont formées par une ou plusieurs gorges de rétention (54) des aubes et formée(s) sur la paroi. Les aubes de la première rangée (24) et le tambour forment un ensemble monobloc, ce qui supprime certaines vibrations. L'ancrage des aubes est hybride ou mixte. Ce rotor peut être monté dans un carter avec des redresseurs formant des bagues.The invention relates to a rotor drum (40) for an axial turbomachine low-pressure compressor. The drum (40) comprises a wall (42) generally symmetrical in revolution about its axis (14) and in a curved general profile. The wall (42) is configured to support multiple rows of vanes (24; 26; 28). A first blade array (24) is formed by an annular platform (46) integrally formed with the wall (42), at the top of its profile with respect to the axis (14); and a second row of blades (26) directly downstream of the first (24) and a third row of blades (28) directly upstream of the first (24), are formed by one or more grooves retainer (54) of the blades and formed on the wall. The blades of the first row (24) and the drum form a unitary assembly, which eliminates certain vibrations. The anchoring of the blades is hybrid or mixed. This rotor can be mounted in a housing with rectifiers forming rings.

Description

Domaine techniqueTechnical area

L'invention a trait à un rotor de turbomachine. Plus précisément, l'invention a trait à un tambour de rotor de compresseur de turbomachine axiale. L'invention a trait à une turbomachine axiale munie d'un tambour de rotor de compresseur basse pression.The invention relates to a turbomachine rotor. More specifically, the invention relates to an axial turbomachine compressor rotor drum. The invention relates to an axial turbomachine with a low pressure compressor rotor drum.

Technique antérieurePrior art

Une turbomachine permet de faire subir à un gaz une compression, une combustion puis une détente. La turbomachine fournit par ce biais une énergie mécanique. Afin d'effectuer ces étapes, la turbomachine comprend un compresseur et une turbine qui sont munis d'un rotor et d'un carter.A turbomachine makes it possible to subject a gas to compression, combustion and relaxation. The turbomachine thereby provides mechanical energy. In order to perform these steps, the turbomachine comprises a compressor and a turbine which are provided with a rotor and a housing.

La surface intérieure du carter et la surface extérieure du rotor dessinent les contours de la veine primaire. Celle-ci présente des variations de sections annulaires. Ses contours intérieurs et extérieurs peuvent augmenter et diminuer de diamètre le long de l'axe de la turbomachine. Au niveau d'un compresseur, notamment du type basse-pression, le carter extérieur présente généralement une diminution de diamètre vers l'aval. D'amont en aval, le rotor peut présenter une augmentation de diamètre, puis une réduction de diamètre. Cette conjugaison de surfaces permet de disposer d'une entrée étendue et d'atteindre un taux de compression élevé en sortie.The inner surface of the housing and the outer surface of the rotor outline the contours of the primary vein. This presents variations of annular sections. Its inner and outer contours can increase and decrease in diameter along the axis of the turbomachine. At the level of a compressor, particularly of the low-pressure type, the outer casing generally has a decrease in diameter downstream. From upstream to downstream, the rotor may have an increase in diameter, and then a reduction in diameter. This combination of surfaces makes it possible to have an extended input and to reach a high compression ratio at the output.

Pour apporter un travail mécanique au fluide, le carter et le rotor du compresseur comprennent, chacun, plusieurs rangées annulaires d'aubes. Les rangées d'aubes rotoriques et les rangées d'aubes statoriques forment axialement une alternance.To provide mechanical work to the fluid, the compressor housing and rotor each comprise several annular rows of blades. The rows of rotor blades and rows of stator vanes axially form an alternation.

Le carter peut comprendre une pluralité de redresseurs annulaires qui comprennent, chacun, une rangée annulaire d'aube. Les redresseurs forment des bagues qui sont rapportées axialement les unes contre les autres en vue de leur fixation. Dans ce cas, chaque aube des rangées rotoriques est fixée au rotor via un pied introduit dans une gorge annulaire formée sur le rotor.The housing may comprise a plurality of annular rectifiers which each comprise an annular array of blades. Rectifiers form rings that are axially reported against each other for attachment. In this case, each blade of the rotor rows is fixed to the rotor via a foot introduced into an annular groove formed on the rotor.

Lors de l'assemblage d'un compresseur avec rotor en forme de tambour, une première rangée d'aube est montée sur le rotor, puis un redresseur annulaire est rapporté axialement en regard de cette première rangée. Ensuite seulement, une deuxième rangée d'aube succédant au redresseur par rapport à la première rangée peut être montée sur le rotor. L'assemblage se poursuit ainsi de suite, en montant tour à tour une rangée d'aubes rotorique et un redresseur. Ce mode d'assemblage est imposé par l'aspect monobloc des redresseurs et par leurs diamètres intérieurs qui ne permettent pas d'y introduire le rotor avec ses aubes.When assembling a compressor with a drum-shaped rotor, a first row of blades is mounted on the rotor, and an annular rectifier is axially attached facing this first row. Then only, a second blade row succeeding the rectifier with respect to the first row can be mounted on the rotor. The assembly continues so on, rising in turn a row of rotor blades and a rectifier. This method of assembly is imposed by the monobloc aspect of the rectifiers and their internal diameters which do not allow to introduce the rotor with its blades.

Le document FR 2 845 436 B1 divulgue un compresseur de turbomachine axiale. Le compresseur comprend un carter externe formé de plusieurs redresseurs rapportés axialement. Il comprend également des rangées annulaires d'aubes qui sont chacune placée entre les redresseurs. Les aubes du rotor sont fixées à l'aide de pieds qui sont insérés dans des saignées annulaires formées dans le rotor. Ce mode de réalisation permet de réaliser un compresseur simple à assembler. Cependant, le rotor est soumis à des vibrations. Il développe des modes vibratoires complexes, difficiles à analyser et à amortir. Par ailleurs, sa réalisation demande des usinages complexes et coûteux. Ajoutons à cela que son architecture reste massive et lourde.The document FR 2 845 436 B1 discloses an axial turbomachine compressor. The compressor comprises an outer casing formed of several rectifiers axially reported. It also includes annular rows of blades which are each placed between the rectifiers. The blades of the rotor are fixed with feet which are inserted into annular grooves formed in the rotor. This embodiment makes it possible to produce a simple compressor to be assembled. However, the rotor is subjected to vibrations. It develops complex vibration modes that are difficult to analyze and dampen. Moreover, its realization requires complex and expensive machining. Add to that that its architecture remains massive and heavy.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

L'invention a pour objectif de résoudre au moins un des problèmes soulevés par l'état de l'art. Plus précisément, l'invention a pour objectif de réduire les vibrations d'un rotor d'une turbomachine axiale. L'invention a également pour objectif d'alléger un rotor de turbomachine axiale.The invention aims to solve at least one of the problems raised by the state of the art. More specifically, the invention aims to reduce the vibrations of a rotor of an axial turbomachine. The invention also aims to lighten an axial turbomachine rotor.

Solution techniqueTechnical solution

L'invention a pour objet un tambour rotorique de turbomachine axiale, notamment de compresseur basse-pression, le tambour comprenant une paroi généralement symétrique en révolution autour de son axe et présentant un profil général courbé, ladite paroi étant configurée pour supporter plusieurs rangées d'aubes ; remarquable en ce qu'une première rangée d'aubes est formée par une plateforme annulaire intégralement formée avec la paroi, au sommet de son profil par rapport à l'axe ; et au moins une, préférentiellement chacune, d'une deuxième rangée d'aubes directement en aval de la première et d'une troisième rangée d'aubes directement en amont de la première, est formée par une ou plusieurs gorges de rétention des aubes, formée(s) sur la paroi.The subject of the invention is an axial turbomachine rotor drum, in particular a low-pressure compressor, the drum comprising a wall that is generally symmetrical in revolution about its axis and having a curved general profile, said wall being configured to support several rows of tubes. blades; remarkable in that a first row of blades is formed by an annular platform integrally formed with the wall at the top of its profile relative to the axis; and at least one, preferably each, of a second row of blades directly downstream of the first and third rows of blades directly upstream of the first, is formed by one or more blade retention grooves, formed on the wall.

Suivant un mode avantageux de l'invention, la surface extérieure de la ou des gorges de rétention est à une distance moyenne de l'axe qui est inférieure à la distance moyenne de la plateforme de la première rangée audit axe.According to an advantageous embodiment of the invention, the outer surface of the retention groove or grooves is at an average distance from the axis which is less than the average distance from the platform of the first row to said axis.

Suivant un mode avantageux de l'invention, la paroi comprend sur sa surface extérieure un jeu de nervures annulaires aptes à coopérer avec une couche annulaire de matériau abradable de sorte à assurer une étanchéité, le jeu de nervure étant disposé axialement entre les première et deuxième rangées d'aubes et/ou entre les première et troisième rangées d'aubes.According to an advantageous embodiment of the invention, the wall comprises on its outer surface a set of annular ribs adapted to cooperate with an annular layer of abradable material so as to ensure a seal, the rib play being arranged axially between the first and second rows of blades and / or between the first and third rows of blades.

Suivant un mode avantageux de l'invention, la distance minimale des sommets d'un des jeux de nervures par rapport à l'axe est supérieure à la distance maximale par rapport audit axe de la surface extérieure de la ou des gorges de rétention adjacente. Il s'agit de la ou des gorges de la deuxième et/ou de la troisième rangée(s) d'aubes.According to an advantageous embodiment of the invention, the minimum distance of the vertices of one of the sets of ribs with respect to the axis is greater than the maximum distance with respect to said axis of the outer surface of the adjacent retention groove or grooves. This is the groove or throats of the second and / or third row (s) of blades.

Suivant un mode avantageux de l'invention, les aubes de la première rangée sont soudées sur la plateforme de ladite rangée.According to an advantageous embodiment of the invention, the blades of the first row are welded to the platform of said row.

Suivant un mode avantageux de l'invention, la plateforme de la première rangée d'aubes comprend des moignons d'aube sur lesquels sont soudées des extensions d'aube, préférentiellement les moignons d'aubes représentent plus de 10% de la hauteur radiale des aubes de la première rangée, plus préférentiellement de plus de 25%.According to an advantageous embodiment of the invention, the platform of the first row of blades comprises blade stubs on which blade extensions are welded, preferentially blade stubs represent more than 10% of the radial height of the blades. blades of the first row, more preferably more than 25%.

Suivant un mode avantageux de l'invention, les aubes de la première rangée sont au moins partiellement taillées dans la masse d'un tambour brut.According to an advantageous embodiment of the invention, the blades of the first row are at least partially cut in the mass of a raw drum.

Suivant un mode avantageux de l'invention, le profil général courbé de la paroi s'étend sur la majeure partie de la longueur du tambour et/ou présente une concavité principale dirigée vers l'axe et s'étendant sur la majeure partie de la longueur du tambour, ledit profil présentant un rayon, par rapport à l'axe, qui est maximum au niveau de la première rangée d'aubes.According to an advantageous embodiment of the invention, the curved general profile of the wall extends over most of the length of the drum and / or has a main concavity directed towards the axis and extending over most of the length of the drum. length of the drum, said profile having a radius, with respect to the axis, which is maximum at the first row of blades.

Suivant un mode avantageux de l'invention, la plateforme de la première rangée d'aubes est surélevée par rapport à la paroi directement en amont et en aval de ladite rangée.According to an advantageous embodiment of the invention, the platform of the first row of blades is raised relative to the wall directly upstream and downstream of said row.

Suivant un mode avantageux de l'invention, la paroi comprend deux portions s'étendant généralement radialement sous la plateforme de la première rangée, de manière à ce que la section longitudinale de la paroi au niveau de ladite plateforme présente un profil en forme de π.According to an advantageous embodiment of the invention, the wall comprises two portions extending generally radially under the platform of the first row, so that the longitudinal section of the wall at said platform has a profile in the form of π. .

Suivant un mode avantageux de l'invention, la paroi comprend au moins un raidisseur annulaire s'étendant radialement vers l'intérieur au niveau de la première rangée d'aubes, préférentiellement dans le prolongement d'au moins une des portions radiales.According to an advantageous embodiment of the invention, the wall comprises at least one annular stiffener extending radially inwards at the first row of blades, preferably in the extension of at least one of the radial portions.

Suivant un mode avantageux de l'invention, la paroi directement en amont et en aval de la première rangée comprend une portion d'épaisseur essentiellement constante qui délimite un espace annulaire destiné à recevoir une virole interne de redresseur.According to an advantageous embodiment of the invention, the wall directly upstream and downstream of the first row comprises a portion of substantially constant thickness which delimits an annular space intended to receive a rectifier inner shell.

Suivant un mode avantageux de l'invention, le tambour rotorique comprend les aubes de la deuxième et/ou de la troisième rangée d'aubes, chacune desdites aubes comprenant un pied logé dans la ou une des gorges de rétention.According to an advantageous embodiment of the invention, the rotor drum comprises the blades of the second and / or third row of blades, each of said blades comprising a foot housed in the or one of the retention grooves.

Suivant un mode avantageux de l'invention, la ou les gorges de rétention sont annulaires suivant le périmètre du tambour.According to an advantageous embodiment of the invention, the retention groove or grooves are annular along the perimeter of the drum.

Suivant un mode avantageux de l'invention, les aubes de la première rangée et la plateforme annulaire forment un ensemble monobloc.According to an advantageous embodiment of the invention, the blades of the first row and the annular platform form a one-piece assembly.

Suivant un mode avantageux de l'invention, le tambour est en matériau métallique, préférentiellement du titane.According to an advantageous embodiment of the invention, the drum is made of metallic material, preferably titanium.

Suivant un mode avantageux de l'invention, la paroi est forgée et taillée dans la masse.According to an advantageous embodiment of the invention, the wall is forged and cut into the mass.

Suivant un mode avantageux de l'invention, la plateforme annulaire et les gorges de rétention sont venues de matière.According to an advantageous embodiment of the invention, the annular platform and the retention grooves are integral.

Suivant un mode avantageux de l'invention, le tambour montre une continuité de matière entre les aubes de la première rangée et la paroi.According to an advantageous embodiment of the invention, the drum shows a continuity of material between the blades of the first row and the wall.

Suivant un mode avantageux de l'invention, un jeu de nervures annulaires est réparti axialement sur la jonction annulaire.According to an advantageous embodiment of the invention, a set of annular ribs is distributed axially on the annular junction.

Suivant un mode avantageux de l'invention, toutes les rangées d'aubes du tambour, hormis la première, comprennent une gorge de rétention des aubes en vue de leur assemblage sur le tambour.According to an advantageous embodiment of the invention, all rows of blades of the drum, except the first, comprise a blade retention groove for assembly on the drum.

L'invention a également trait à une turbomachine axiale comprenant un tambour rotorique, remarquable en ce que le tambour est conforme à l'invention, préférentiellement le rotor est un rotor de compresseur basse pression comprenant essentiellement trois rangées annulaires d'aubes rotoriques.The invention also relates to an axial turbomachine comprising a rotor drum, remarkable in that the drum is in accordance with the invention, preferably the rotor is a low-pressure compressor rotor comprising essentially three annular rows of rotor blades.

Avantages apportésBenefits brought

L'invention permet de réduire les vibrations d'un rotor de turbomachine axiale. Pour cela elle supprime la liberté de mouvement entre la paroi annulaire et les aubes de la première rangée. L'invention améliore au passage la rigidité générale du tambour. L'architecture proposée permet en outre d'alléger le rotor, en agissant à la fois sur le tambour et sur les aubes.The invention makes it possible to reduce the vibrations of an axial turbomachine rotor. For this it removes the freedom of movement between the annular wall and the blades of the first row. The invention improves the overall rigidity of the drum. The proposed architecture also makes it possible to lighten the rotor, by acting on both the drum and the blades.

Les usinages des surfaces du tambour et des aubes sont simplifiés. Toutes ces améliorations du tambour deviennent possibles tout en conservant la compatibilité du rotor avec un carter formé de redresseurs annulaires.The machining of the surfaces of the drum and the blades are simplified. All these improvements of the drum become possible while maintaining the compatibility of the rotor with a housing formed of annular rectifiers.

L'invention est appliquée à un tambour muni de nervures annulaires en guise de moyen d'étanchéité entre les étages de compression. Cet aspect n'est pas limitatif puisque l'invention peut également être appliquée à un tambour coopérant avec des joints à brosses axiales. Des tels joints sont bien connus de l'homme du métier et peuvent, par exemple, correspondre à ceux divulgués dans le document DE102005042272 A1 .The invention is applied to a drum provided with annular ribs as a sealing means between the compression stages. This aspect is not limiting since the invention can also be applied to a drum cooperating with axial brush seals. Such seals are well known to those skilled in the art and may, for example, correspond to those disclosed in the document DE102005042272 A1 .

Brève description des dessinsBrief description of the drawings

La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.

La figure 2 est un schéma d'un compresseur de turbomachine selon l'invention.The figure 2 is a diagram of a turbomachine compressor according to the invention.

La figure 3 illustre une section du tambour de rotor selon l'invention.The figure 3 illustrates a section of the rotor drum according to the invention.

Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes intérieur ou interne et extérieur ou externe renvoient à un positionnement par rapport à l'axe de rotation de la turbomachine axiale.In the following description, the terms inner or inner and outer or outer refer to a positioning relative to the axis of rotation of the axial turbomachine.

La figure 1 représente de manière simplifiée une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un premier niveau de compression, dit compresseur basse-pression 4, un deuxième niveau de compression, dit compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 4 et 6. Des moyens de démultiplication peuvent augmenter la vitesse de rotation transmise aux compresseurs. Alternativement, les différents étages de turbines peuvent chacun être reliés aux étages de compresseur via des arbres concentriques. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stators. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 10.The figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine. The turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. Reducing means can increase the speed of rotation transmitted to the compressors. Alternatively, the different turbine stages can each be connected to the compressor stages via concentric shafts. The latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 10.

Un ventilateur d'entrée communément désigné fan 16 est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 traversant les différents niveaux sus mentionnés de la turbomachine, et un flux secondaire 20 traversant un conduit annulaire (partiellement représenté) le long de la machine pour ensuite rejoindre le flux primaire en sortie de turbine. Les flux primaire 18 et secondaire 20 sont des flux annulaires, ils sont canalisés par le carter de la turbomachine. A cet effet, le carter présente des parois cylindriques ou viroles qui peuvent être internes et externes.A commonly designated fan inlet fan 16 is coupled to the rotor 12 and generates a flow of air which is divided into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow out of turbine. The primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine. For this purpose, the casing has cylindrical walls or ferrules which can be internal and external.

La figure 2 est une vue en coupe d'un compresseur d'une turbomachine axiale 2 telle que celle de la figure 1. Le compresseur peut être un compresseur basse pression 4. L'enseignement de la présente invention peut également être appliqué à un tambour de rotor de turbine 10.The figure 2 is a sectional view of a compressor of an axial turbomachine 2 such as that of the figure 1 . The compressor may be a low pressure compressor 4. The teaching of the present invention may also be applied to a turbine rotor drum 10.

On peut observer sur le compresseur 4 un bec de séparation 22 du flux primaire 18 et du flux secondaire 20. Le rotor 12 comprend plusieurs rangées annulaires d'aubes rotoriques, dans le cas précis de la figure 2, trois rangées sont prévues. D'avantage de rangées d'aubes peuvent être prévues. Ces trois rangées sont axialement successives. On observe une première rangée d'aubes rotoriques 24, une deuxième rangée d'aubes rotoriques 26 en aval de la première rangée 24 et une troisième rangée d'aubes rotoriques 28 en amont de la première rangée 24.It is possible to observe on the compressor 4 a separation nozzle 22 of the primary flow 18 and of the secondary flow 20. The rotor 12 comprises several annular rows of rotor blades, in the specific case of the figure 2 three rows are planned. More rows of vanes can be provided. These three rows are axially successive. A first row of rotor blades 24, a second row of rotor blades 26 downstream of the first row 24 and a third row of rotor blades 28 upstream of the first row 24 are observed.

Les aubes rotoriques (24, 26, 28) s'étendent essentiellement radialement depuis le rotor 12. Les aubes d'une même rangée sont régulièrement espacés les unes des autres, et présentent une même orientation angulaire dans le flux. Eventuellement, l'espacement entre les aubes peut varier localement, tout comme leur orientation angulaire. Certaines aubes peuvent être différentes du reste des aubes de la rangée correspondante.The rotor blades (24, 26, 28) extend substantially radially from the rotor 12. The blades of the same row are regularly spaced from each other, and have the same angular orientation in the flow. Optionally, the spacing between the vanes may vary locally, as can their angular orientation. Some blades may be different from the rest of the blades of the corresponding row.

Le compresseur 4 comprend un carter extérieur. Le carter extérieur comprend plusieurs redresseurs, par exemple quatre, qui comportent chacun, une virole externe 30, une rangée d'aubes statoriques 32 et éventuellement un virole interne 34. Une couche annulaire de matériau abradable 36 peut être appliquée à l'intérieur de la virole externe et de la virole interne d'un redresseur. Les aubes statoriques 32 d'un même redresseur s'étendent radialement depuis leur virole externe 30 vers leur virole interne 34. Les redresseurs forment des bagues fermées circulairement. Ils sont rapportés axialement les uns contre les autres et fixés les uns aux autres à l'aide de brides radiales 38.The compressor 4 comprises an outer casing. The outer casing comprises a plurality of rectifiers, for example four, which each comprise an outer shell 30, a row of stator vanes 32 and optionally an inner shell 34. An annular layer of abradable material 36 may be applied inside the shell. outer shell and the inner shell of a rectifier. The stator vanes 32 of the same rectifier extend radially from their outer shell 30 to their inner shell 34. The rectifiers form circularly closed rings. They are reported axially against each other and fixed to each other by means of radial flanges 38.

Les redresseurs sont associés au fan ou à une rangée d'aubes rotoriques (24, 26, 28) pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression.The rectifiers are associated with the fan or a row of rotor vanes (24, 26, 28) for straightening the airflow, so as to convert the speed of the flow into pressure.

Le rotor 12 comprend un tambour 40. Le tambour 40 comporte une paroi 42 généralement symétrique en révolution autour de son axe de rotation 14, axe qui est commun avec celui de la turbomachine. La paroi 42 peut présenter un profil général de révolution ou profil moyen de révolution autour de l'axe de rotation 14. Le profil général peut être compris dans l'épaisseur des portions de la paroi 42 qui sont au droit axialement des rangées d'aubes statoriques.The rotor 12 comprises a drum 40. The drum 40 comprises a wall 42 generally symmetrical in revolution about its axis of rotation 14, which axis is common with that of the turbomachine. The wall 42 may have a general profile of revolution or average profile of revolution about the axis of rotation 14. The general profile may be included in the thickness of the portions of the wall 42 which are axially right rows of vanes stator.

Le profil général est essentiellement courbé et peut présenter une courbure continue et/ou une variation de courbure continue. Il suit radialement la variation de section de la surface intérieure du flux primaire 18. L'extérieur du profil général est convexe. D'amont en aval, le rayon de la surface intérieure croît puis diminue, de sorte que le profil de la paroi présente un sommet. La paroi 42 est essentiellement fine. Son épaisseur est généralement constante. Son épaisseur est inférieure à 10,00 mm, préférentiellement inférieure à 5,00 mm, plus préférentiellement inférieure à 2,00 mm. La paroi 42 forme un corps creux qui délimite un espace creux, ayant une forme d'ogive ou de tonnelet. Le tambour 40 et/ou les aubes rotoriques (24, 26, 28) sont réalisés en matériaux métallique, préférentiellement en titane.The overall profile is essentially curved and may have a continuous curvature and / or a continuous curvature variation. It follows radially the section variation of the inner surface of the primary stream 18. The outside of the general profile is convex. From upstream to downstream, the radius of the inner surface increases and then decreases, so that the profile of the wall has a peak. The wall 42 is essentially thin. Its thickness is generally constant. Its thickness is less than 10.00 mm, preferably less than 5.00 mm, more preferably less than 2.00 mm. The wall 42 forms a hollow body which delimits a hollow space, having an ogive or barrel shape. The drum 40 and / or the rotor blades (24, 26, 28) are made of metallic materials, preferably of titanium.

Le tambour 40 comprend des nervures annulaires 44 ou léchettes. Elles forment des lamelles annulaires qui s'étendent radialement. Elles sont destinées à coopérer par abrasion avec des couches annulaires de matériau abradable 36 d'un redresseur de sorte à assurer une étanchéité. Généralement, une même couche d'abradable 36 coopère avec deux nervures annulaires 44.The drum 40 comprises annular ribs 44 or wipers. They form annular lamellae which extend radially. They are intended to cooperate by abrasion with annular layers of abradable material 36 of a rectifier so as to ensure a seal. Generally, one and the same abradable layer 36 cooperates with two annular ribs 44.

La figure 3 est vue de détail en coupe du tambour 40 de la figure 2. Le tambour peut également être un tambour de rotor de compresseur haute pression. Il peut éventuellement être un tambour de rotor de turbine.The figure 3 is detail view in section of the drum 40 of the figure 2 . The drum may also be a high pressure compressor rotor drum. It may possibly be a turbine rotor drum.

La première rangée d'aubes 24 est formée sur la paroi par une plateforme annulaire 46. La plateforme annulaire 46 est intégralement formée avec la paroi 42. La plateforme annulaire 46 est formée au sommet du profil de la paroi 42. La plateforme annulaire 46 a un profil de révolution généralement droit ou sensiblement courbé.The first row of vanes 24 is formed on the wall by an annular platform 46. The annular platform 46 is integrally formed with the wall 42. The annular platform 46 is formed at the top of the profile of the wall 42. The annular platform 46 has a generally straight or substantially curved profile of revolution.

Les aubes rotoriques de la deuxième rangée 26 et de la troisième rangée 28 comprennent chacune une plateforme d'aube 48 délimitant l'intérieur du flux primaire, une pale 50 s'étendant radialement vers l'extérieur depuis la plateforme d'aube 46, et un pied de rétention 52 s'étendant radialement vers l'intérieur depuis la plateforme d'aube 48. Le pied de rétention 52 peut présenter une forme en queue d'aronde. Il peut présenter une forme dont la dimension axiale augmente lorsque l'on se rapproche de l'intérieur, de sorte à permettre en engagement de matière.The rotor blades of the second row 26 and the third row 28 each comprise a blade platform 48 defining the inside of the primary flow, a blade 50 extending radially outwardly from the blade platform 46, and a retention foot 52 extending radially inwardly from the blade platform 48. The retention foot 52 may have a dovetail shape. It may have a shape whose axial dimension increases when one gets closer to the interior, so as to allow commitment of material.

La paroi 42 du tambour 40 comprend deux zones de fixation d'aubes par gorge de rétention. Les zones de fixation comprennent chacune une gorge annulaire 54 dans laquelle sont introduits les pieds de rétention 52 des aubes de la deuxième rangée 26 et de la troisième rangée 28. Les gorges annulaires 54 comprennent des surfaces extérieures annulaires contre lesquelles viennent en contact les plateformes d'aubes 48. Les plateformes d'aubes 48 de la deuxième rangée d'aubes 26 viennent en contact de la deuxième surface extérieure 56, et les plateformes d'aubes 48 la troisième rangée d'aubes 28 viennent en contact de la troisième surface extérieure 58.The wall 42 of the drum 40 comprises two blade attachment zones by retention groove. The fixing zones each comprise an annular groove 54 into which the retention feet 52 of the blades of the second row 26 and of the third row 28 are introduced. The annular grooves 54 comprise annular outer surfaces against which the platforms of 48. The blade platforms 48 of the second row of blades 26 come into contact with the second outer surface 56, and the blade platforms 48 the third row of blades 28 come into contact with the third outer surface. 58.

Les pieds de rétention 52 présentent généralement une forme complémentaire de la gorge de rétention correspondante, de sorte à assurer une rétention radiale. Les gorges de rétention 54 présentent un profil avec un rétrécissement au niveau de leur sortie, vers l'extérieur. Ainsi, les aubes de la deuxième rangée 26 et de la troisième rangée 28 sont retenues selon un mode réversible. Un jeu mécanique est prévu entre la paroi annulaire 42 et les aubes rotoriques de la deuxième et de la troisième rangée, de sorte à autoriser un léger mouvement des aubes. Cependant, le rotor est configuré de manière à ce que la force centrifuge présente lors du fonctionnement du compresseur plaque en position les aubes dans leur gorge.The retention feet 52 generally have a shape complementary to the corresponding retention groove, so as to ensure radial retention. The retention grooves 54 have a profile with a narrowing at their outlet, to the outside. Thus, the blades of the second row 26 and the third row 28 are retained in a reversible mode. A mechanical clearance is provided between the annular wall 42 and the rotor blades of the second and third rows, so as to allow a slight movement of the blades. However, the rotor is configured so that the centrifugal force present during operation of the plate compressor in position the blades in their groove.

Suivant une alternative de l'invention les gorges de rétention peuvent être des gorges axiales. La paroi annulaire comporte alors une rangée annulaire de gorges axiales réparties sur sa circonférence, et qui forment chacune une rangée annulaire d'aubes.According to an alternative of the invention, the retention grooves may be axial grooves. The annular wall then comprises an annular row of axial grooves distributed over its circumference, and which each form an annular row of vanes.

La surface extérieure (56, 58) d'au moins une des gorges annulaires 48 est à une distance moyenne de l'axe 14 qui est inférieure à la distance moyenne de la plateforme annulaire 46 de la première rangée 24 dudit axe. Préférentiellement, chaque rayon d'une extrémité axiale de la plateforme annulaire 46 est supérieur au rayon maximal de la surface extérieure (56, 58) disposée en regard.The outer surface (56, 58) of at least one of the annular grooves 48 is at an average distance from the axis 14 which is less than the average distance from the annular platform 46 of the first row 24 of said axis. Preferably, each radius of an axial end of the annular platform 46 is greater than the maximum radius of the outer surface (56, 58) disposed opposite.

Les aubes de la première rangée 24 sont ancrées sur le tambour selon un mode différent des autres rangées (26 ; 28). La rétention ou la fixation des aubes est hétérogène ou hybride. Les aubes de la première rangée 24 sont fixées par soudage sur la plateforme annulaire 46. Elles peuvent être soudées par friction, par exemple selon un procédé de soudure orbital. Le tambour 40 sert donc de support de fixation à deux types d'aubes.The blades of the first row 24 are anchored to the drum in a different fashion from the other rows (26; 28). The retention or fixation of the blades is heterogeneous or hybrid. The blades of the first row 24 are fixed by welding on the annular platform 46. They can be friction welded, for example by an orbital welding process. The drum 40 thus serves as a support for fixing two types of blades.

A cet effet, des aubes correspondant à la première rangée 24 sont rapportées sur un tambour brut et soudées sur la plateforme annulaire 46. Ces aubes peuvent être directement ou indirectement rapportées sur la plateforme annulaire 46. La plateforme annulaire 46 peut comprendre des moignons d'aubes 60 qui s'étendant radialement depuis sa surface extérieure. Dans ce cas, chaque aube qui est soudée sur la deuxième surface ne forme en réalité qu'une portion radiale de l'aube finale. La soudure 62 entre un moignon et une portion d'aube est en élévation par rapport à la plateforme annulaire 46.For this purpose, blades corresponding to the first row 24 are attached to a raw drum and welded to the annular platform 46. These vanes can be directly or indirectly attached to the annular platform 46. The annular platform 46 may include stubs. blades 60 which extend radially from its outer surface. In this case, each blade which is welded to the second surface actually forms only a radial portion of the final blade. The weld 62 between a stump and a blade portion is in elevation relative to the annular platform 46.

Selon une alternative de l'invention, les aubes de la première rangée 24 peuvent être intégralement usinées dans la masse d'un tambour brut dans lequel est également usinée la paroi.According to an alternative of the invention, the blades of the first row 24 can be integrally machined in the mass of a raw drum in which the wall is also machined.

Ainsi, la paroi du tambour 40 et les aubes 24 de la première rangée forment un ensemble monobloc. Elles présentent une continuité de matière. Leurs matériaux métalliques présentent une continuité cristalline à leur interface. Ils peuvent être au moins partiellement venus de matière. L'ancrage des aubes est irréversible. Les aubes de la première rangée 24 sont solidaires de la paroi annulaire 42. Ce mode de réalisation permet de supprimer des vibrations entre les aubes de la première rangée 26 et la paroi 42 du tambour 40.Thus, the wall of the drum 40 and the blades 24 of the first row form a one-piece assembly. They present a continuity of matter. Their metallic materials have a crystalline continuity at their interface. They can be at least partially come from matter. The anchoring of the vanes is irreversible. The blades of the first row 24 are integral with the annular wall 42. This embodiment makes it possible to eliminate vibrations between the blades of the first row 26 and the wall 42 of the drum 40.

De plus, ce mode d'ancrage des aubes simplifie les usinages à réaliser car la plateforme annulaire 46 et les éventuels moignons 60 sont plus simples à réaliser qu'une gorge annulaire ou que plusieurs gorges axiales. En effet, une gorge doit être taillée dans un espace généralement peu accessible avec un outil de petite taille, ce qui rallonge le temps de fabrication. Ou alors, une gorge axiale peut être usinée par brochage. Cependant, ce procédé d'enlèvement de matière demande un outillage coûteux et n'est pas compatible avec toutes les formes de tambour.In addition, this method of anchoring the blades simplifies the machining to be performed because the annular platform 46 and any stubs 60 are simpler to achieve than an annular groove or several axial grooves. Indeed, a groove must be cut in a generally inaccessible space with a small tool, which lengthens the manufacturing time. Or, an axial groove can be machined by broaching. However, this material removal process requires expensive tooling and is not compatible with all drum shapes.

La paroi 42 du tambour directement en amont et en aval de la première rangée d'aubes 24 comprend au moins une portion d'épaisseur essentiellement constante 64 ou jonction annulaire axiale 64, préférentiellement deux portions d'épaisseurs essentiellement constantes 64. Chaque portion d'épaisseur constante 64 s'étend axialement depuis la plateforme annulaire 46 vers la deuxième rangée d'aubes 26 ou vers la troisième rangée d'aubes 28. La plateforme annulaire 46 est radialement en élévation annulaire par rapport à chaque portion d'épaisseur constante 64. Les portions d'épaisseurs constantes 64 délimitent un espace annulaire entre la première rangée d'aubes 26 et la deuxième rangée d'aubes 28 ou la troisième rangée d'aubes 24, ces espaces annulaires étant ouverts radialement vers l'extérieur. Ils sont destinés à loger des viroles internes de redresseurs.The wall 42 of the drum directly upstream and downstream of the first row of blades 24 comprises at least one portion of substantially constant thickness 64 or axial annular junction 64, preferably two portions of essentially constant thicknesses 64. Each portion of constant thickness 64 extends axially from the annular platform 46 to the second row of blades 26 or to the third row of blades 28. The annular platform 46 is radially in annular elevation with respect to each portion of constant thickness 64. The portions of constant thicknesses 64 define an annular space between the first row of blades 26 and the second row of blades 28 or the third row of blades 24, these annular spaces being open radially outwardly. They are intended to house internal ferrules of rectifiers.

La paroi 42 comprend deux portions 65 qui s'étendent généralement radialement. Elles s'étendent depuis la plateforme annulaire 46 vers l'intérieur. Elles peuvent chacune être disposée à un des bords axiaux de la plateforme annulaire 46. De la sorte, la paroi peut présenter un profil de général de la lettre grecque π. Les profils des portions radiales s'étendent généralement perpendiculairement au profil de la plateforme annulaire 46.The wall 42 comprises two portions 65 which extend generally radially. They extend from the annular platform 46 inwards. They may each be arranged at one of the axial edges of the annular platform 46. In this way, the wall may have a profile of the general Greek letter π. The profiles of the radial portions extend generally perpendicular to the profile of the annular platform 46.

Les nervures annulaires 44 sont disposées sur les portions d'épaisseurs constantes 64. Chaque jeu de nervure comprend plusieurs nervures 44. De chaque côté de la plateforme annulaire 46 on observe une diminution progressive des rayons extérieurs depuis un bord de la plateforme annulaire 46, des nervures 44, puis des surfaces extérieures (56 ; 58) des gorges annulaires. Les sommets de ces éléments forment un escalier. Cette configuration permet de rapporter des redresseurs aubagés de part et d'autre de la première rangée d'aubes 24, puis de monter la deuxième rangée 26 et la troisième rangée 28.The annular ribs 44 are arranged on the portions of constant thicknesses 64. Each rib set comprises several ribs 44. On each side of the annular platform 46 there is a decrease progressive outer rays from an edge of the annular platform 46, ribs 44, and outer surfaces (56; 58) of the annular grooves. The tops of these elements form a staircase. This configuration makes it possible to report bladed rectifiers on either side of the first row of blades 24, then to assemble the second row 26 and the third row 28.

La figure 3 illustre les aubes 32 et la virole interne 36 des deux redresseurs en amont et en aval, respectivement, de la première rangée d'aubes 24. La figure 3 illustre également en trait interrompu ces redresseurs dans une position intermédiaire de montage, selon une direction axiale, autour du tambour.The figure 3 illustrates the blades 32 and the inner shroud 36 of the two rectifiers upstream and downstream, respectively, of the first row of blades 24. The figure 3 also shows in broken lines these rectifiers in an intermediate position of assembly, in an axial direction, around the drum.

La paroi annulaire 42 du tambour comprend des raidisseurs annulaires 66. Les raidisseurs annulaires 66 peuvent comprendre des brides annulaires qui s'étendent radialement vers l'intérieur. Ces brides sont disposées axialement au niveau des extrémités de la plateforme annulaire 46, préférentiellement dans le prolongement radial des portions radiales 65.The annular wall 42 of the drum includes annular stiffeners 66. The annular stiffeners 66 may include annular flanges that extend radially inwardly. These flanges are arranged axially at the ends of the annular platform 46, preferably in the radial extension of the radial portions 65.

Le tambour est généralement usiné par tournage à partir d'un brut d'usinage en forme de tambour dont les parois englobent le tambour fini. Le tambour brut doit englober radialement les surfaces extérieures des gorges annulaires 54, la plateforme annulaire 46, les raidisseurs intérieurs 66, et les éventuels moignons d'aubes 60. Selon le cas, il peut englober les aubes de la première rangée 54 sur toute leur hauteur radiale.The drum is generally machined by turning from a drum-shaped machining blank whose walls encompass the finished drum. The raw drum must radially encompass the outer surfaces of the annular grooves 54, the annular platform 46, the internal stiffeners 66, and any blade stubs 60. As the case may be, it may encompass the blades of the first row 54 over their entire length. radial height.

Claims (15)

Tambour rotorique (40) de turbomachine axiale (2), notamment de compresseur basse-pression (4), le tambour (40) comprenant une paroi (42) généralement symétrique en révolution autour de son axe (14) et présentant un profil général courbé, ladite paroi (42) étant configurée pour supporter plusieurs rangées d'aubes (24 ; 26 ; 28) ;
caractérisé en ce que
une première rangée d'aubes (24) est formée par une plateforme annulaire (46) intégralement formée avec la paroi (42), au sommet de son profil par rapport à l'axe (14); et au moins une, préférentiellement chacune, d'une deuxième rangée d'aubes (26) directement en aval de la première (24) et d'une troisième rangée d'aubes (28) directement en amont de la première (24), est formée par une ou plusieurs gorges de rétention (54) des aubes, formée(s) sur la paroi.Rotor drum (40) for an axial turbomachine (2), in particular a low-pressure compressor (4), the drum (40) comprising a wall (42) generally symmetrical in revolution about its axis (14) and having a curved general profile said wall (42) being configured to support a plurality of rows of vanes (24; 26; 28);
characterized in that
a first blade array (24) is formed by an annular platform (46) integrally formed with the wall (42), at the top of its profile with respect to the axis (14); and at least one, preferably each, of a second row of blades (26) directly downstream of the first (24) and a third row of blades (28) directly upstream of the first (24), is formed by one or more retention grooves (54) of the vanes formed on the wall. Tambour rotorique (40) selon la revendication 1, caractérisé en ce que la surface extérieure (56 ; 58) de la ou des gorges de rétention (54) est à une distance moyenne de l'axe (14) qui est inférieure à la distance moyenne de la plateforme (46) de la première rangée (24) audit axe.Rotor drum (40) according to claim 1, characterized in that the outer surface (56; 58) of the at least one retention groove (54) is at an average distance from the axis (14) which is less than the distance average of the platform (46) of the first row (24) to said axis. Tambour rotorique (40) selon l'une des revendications 1 et 2, caractérisé en ce que la paroi (42) comprend sur la surface extérieure un jeu de nervures annulaires (44) aptes à coopérer avec une couche annulaire de matériau abradable (36) de sorte à assurer une étanchéité, le jeu de nervure (44) étant disposé axialement entre les première (24) et deuxième (26) rangées d'aubes et/ou entre les première (24) et troisième (28) rangées d'aubes.Rotor drum (40) according to one of claims 1 and 2, characterized in that the wall (42) comprises on the outer surface a set of annular ribs (44) adapted to cooperate with an annular layer of abradable material (36) to provide a seal, the rib clearance (44) being disposed axially between the first (24) and second (26) rows of blades and / or between the first (24) and third (28) rows of vanes . Tambour rotorique (40) selon la revendication 3, caractérisé en ce que la distance minimale des sommets d'un des jeux de nervures (44) par rapport à l'axe (14) est supérieure à la distance maximale par rapport audit axe (14) de la surface extérieure (56 ; 58) de la ou des gorges de rétention (54) adjacente.Rotor drum (40) according to claim 3, characterized in that the minimum distance of the peaks of one of the sets of ribs (44) from the axis (14) is greater than the maximum distance from said axis (14). ) of the outer surface (56; 58) of the adjacent one or more retention grooves (54). Tambour rotorique (40) selon l'une des revendications 1 à 4, caractérisé en ce que les aubes de la première rangée (24) sont soudées sur la plateforme (46) de ladite rangée.Rotor drum (40) according to one of claims 1 to 4, characterized in that the blades of the first row (24) are welded to the platform (46) of said row. Tambour rotorique (40) selon l'une des revendications 1 à 4, caractérisé en ce que la plateforme (46) de la première rangée d'aubes (24) comprend des moignons (60) d'aube sur lesquels sont soudées des extensions d'aube, préférentiellement les moignons d'aubes (60) représentent plus de 10% de la hauteur radiale des aubes de la première rangée (24), plus préférentiellement de plus de 25%.Rotor drum (40) according to one of claims 1 to 4, characterized in that the platform (46) of the first row of vanes (24) comprises blade stubs (60) on which are welded extensions of dawn, preferably the blade stubs (60) represent more than 10% of the radial height of the blades of the first row (24), more preferably more than 25%. Tambour rotorique (40) selon l'une des revendications 1 à 6, caractérisé en ce que les aubes de la première rangée (24) sont au moins partiellement taillées dans la masse d'un tambour brut.Rotor drum (40) according to one of claims 1 to 6, characterized in that the blades of the first row (24) are at least partially cut into the mass of a raw drum. Tambour rotorique (40) selon l'une des revendications 1 à 8, caractérisé en ce que le profil général courbé de la paroi (42) s'étend sur la majeure partie de la longueur du tambour et/ou présente une concavité principale dirigée vers l'axe et s'étendant sur la majeure partie de la longueur du tambour, ledit profil présentant un rayon maximum au niveau de la première rangée d'aubes (24).Rotor drum (40) according to one of claims 1 to 8, characterized in that the curved general profile of the wall (42) extends over most of the length of the drum and / or has a main concavity directed towards the axis and extending over most of the length of the drum, said profile having a maximum radius at the first row of blades (24). Tambour rotorique (40) selon l'une des revendications 1 à 8, caractérisé en ce que la plateforme (46) de la première rangée d'aubes (24) est surélevée par rapport à la paroi directement en amont et en aval de ladite rangée.Rotor drum (40) according to one of claims 1 to 8, characterized in that the platform (46) of the first row of blades (24) is raised relative to the wall directly upstream and downstream of said row . Tambour rotorique (40) selon la revendication 9, caractérisé en ce que la paroi (42) comprend deux portions (65) s'étendant généralement radialement sous la plateforme (46) de la première rangée (24), de manière à ce que la section longitudinale de la paroi (42) au niveau de ladite plateforme (46) présente un profil en forme de π.Rotor drum (40) according to claim 9, characterized in that the wall (42) comprises two portions (65) extending generally radially under the platform (46) of the first row (24), so that the longitudinal section of the wall (42) at said platform (46) has a profile in the form of π. Tambour rotorique (40) selon la revendication 10, caractérisé en ce que la paroi (42) comprend au moins un raidisseur annulaire (66) s'étendant radialement vers l'intérieur au niveau de la première rangée d'aubes (24), préférentiellement dans le prolongement d'au moins une des portions radiales (65).Rotor drum (40) according to claim 10, characterized in that the wall (42) comprises at least one annular stiffener (66) extending radially inwards at the first row of vanes (24), preferably in the extension of at least one of the radial portions (65). Tambour rotorique (40) selon l'une des revendications 9 à 11, caractérisé en ce que la paroi (42) directement en amont et en aval de la première rangée (24) comprend une portion d'épaisseur essentiellement constante (64) qui délimite un espace annulaire destiné à recevoir une virole interne (34) de redresseur.Rotor drum (40) according to one of claims 9 to 11, characterized in that the wall (42) directly upstream and downstream of the first row (24) comprises a portion of substantially constant thickness (64) which defines an annular space for receiving a rectifier inner shell (34). Tambour rotorique (40) selon l'une des revendications 1 à 12, caractérisé en ce qu'il comprend les aubes de la deuxième et/ou de la troisième rangée d'aubes, chacune desdites aubes comprenant un pied (52) logé dans la ou une des gorges de rétention (54).Rotor drum (40) according to one of claims 1 to 12, characterized in that it comprises the blades of the second and / or third row of blades, each of said vanes comprising a foot (52) housed in the or one of the retention grooves (54). Tambour rotorique (40) selon l'une des revendications 1 à 13, caractérisé en ce que la ou les gorges de rétention (54) sont annulaires suivant le périmètre du tambour (40).Rotor drum (40) according to one of claims 1 to 13, characterized in that the retention groove or grooves (54) are annular along the perimeter of the drum (40). Turbomachine (2) axiale comprenant un tambour rotorique (40), caractérisée en ce que le tambour (40) est conforme à l'une des revendications 1 à 14, préférentiellement le rotor (12) est un rotor de compresseur basse pression (4) comprenant essentiellement trois rangées annulaires d'aubes rotoriques (24 ; 26 ; 28).Axial turbine engine (2) comprising a rotor drum (40), characterized in that the drum (40) is according to one of claims 1 to 14, preferably the rotor (12) is a low-pressure compressor rotor (4) essentially comprising three annular rows of rotor vanes (24; 26; 28).
EP13173510.2A 2013-06-25 2013-06-25 Drum of axial turbomachine compressor with mixed fixation of blades Active EP2818635B1 (en)

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EP13173510.2A EP2818635B1 (en) 2013-06-25 2013-06-25 Drum of axial turbomachine compressor with mixed fixation of blades
CA2853663A CA2853663A1 (en) 2013-06-25 2014-06-09 Axial turbomachine compressor drum with dual means of blade fixing
RU2014125101/02A RU2576354C2 (en) 2013-06-25 2014-06-20 Compressor drum of axial turbine machine with double device for blade locking
US14/315,097 US20140377070A1 (en) 2013-06-25 2014-06-25 Axial Turbomachine Compressor Drum with Dual Means of Blade Fixing
CN201410290159.1A CN104251232B (en) 2013-06-25 2014-06-25 Axial flow turbo-machine compressor drum with blades double fixed form

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US20140377070A1 (en) 2014-12-25
CN104251232B (en) 2019-04-30
RU2014125101A (en) 2015-12-27
RU2576354C2 (en) 2016-02-27

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