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EP2614258A1 - Turbojet casing and turbojet receiving such casings - Google Patents

Turbojet casing and turbojet receiving such casings

Info

Publication number
EP2614258A1
EP2614258A1 EP11754367.8A EP11754367A EP2614258A1 EP 2614258 A1 EP2614258 A1 EP 2614258A1 EP 11754367 A EP11754367 A EP 11754367A EP 2614258 A1 EP2614258 A1 EP 2614258A1
Authority
EP
European Patent Office
Prior art keywords
housing
blades
blade
turbojet
casing
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.)
Withdrawn
Application number
EP11754367.8A
Other languages
German (de)
French (fr)
Inventor
Patrick Dunleavy
Richard Masson
Bertrand Desjoyeaux
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 Nacelles SAS
Safran Landing Systems SAS
Original Assignee
Messier Bugatti Dowty SA
Aircelle 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 Messier Bugatti Dowty SA, Aircelle SA filed Critical Messier Bugatti Dowty SA
Publication of EP2614258A1 publication Critical patent/EP2614258A1/en
Withdrawn legal-status Critical Current

Links

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a turbojet casing adapted to receive a plurality of blades and a turbojet incorporating such casings.
  • Annular housings are known comprising attachment means intended to cooperate with the ends of a blade.
  • the document US2009 / 0317246 recommends ends having a cylindrical platform forming a portion of the outer casing and carrying two fixing flanks, which leads to complex shapes to manufacture.
  • the document US2009 / 0317246 recommends the joining of the blades together by means of a circular ring before mounting the assembly thus formed in the housing. This is a cumbersome solution to implement, requiring assembly tools.
  • the object of the invention is therefore to provide a turbojet casing simple to produce and easy to assemble.
  • a turbojet engine housing adapted to receive a plurality of blades, comprising means for hooking an end of each blade on the housing.
  • the attachment means extend on one face of the housing opposite the blades, the casing has orifices for passing the ends of the blades so that they can cooperate with the attachment means of the housing.
  • the means fastening means comprise an annular member extending around the casing, the casing comprising long fibers and thermoplastic resin, and the annular member being obtained by pultrusion and impregnated with a thermoplastic resin weldable with the thermoplastic resin of the housing, assembly being assembled by hot compaction. This gives the whole a strong cohesion.
  • the invention also relates to a turbojet comprising at least one housing according to the invention and a plurality of blades each having an end connected to the housing.
  • each blade comprises:
  • At least one of the leading edge or the trailing edge has extensions which project from the web at least on one side of the blade, to carry hooking means cooperating with the means attachment of the turbojet casing.
  • FIG. 1 is a top view of a blade to be fixed to a housing according to the invention
  • FIG. 2 is a perspective view of the blade of Figure 1, the skin covering the soul of the blade being partially cut away;
  • Figure 3 is a perspective view of a first mode of attachment of the blade to a housing according to the invention.
  • FIG. 4 is a perspective view of a second mode of fixing the blade to the casing according to the invention.
  • the blade 1 which is illustrated here is a stator blade, intended to extend behind the fan of a turbojet engine.
  • the blade 1 comprises a leading edge 2 which is here in the form of an elongate monobloc structure.
  • the blade 1 further comprises a trailing edge 3 which is also in the form of an elongate monobloc structure.
  • the leading edge 2 and the trailing edge 3 are cut in profiles obtained by pultrusion, preferably with oblique fiber placement (so-called "pullbraiding” process).
  • the profiles comprise fibers, for example carbon fibers, substantially disposed along a longitudinal axis to form an elongated body. Ideally, substantially 80% of the fibers are disposed along the longitudinal axis of the leading edge X and leakage Y and 20% of the fibers are disposed at an inclination of about 60 degrees to the longitudinal axis. These proportions and the arrangement of the fibers are given by way of example.
  • the fibers are here impregnated with thermoplastic resin. Between the leading edge 2 and the trailing edge 3 extends a core 4.
  • a skin 5 comprising here two webs 5A, 5B obtained by cutting in a fiber fabric cross ⁇ impregnated with thermoplastic resin, extend from and other of the core 4 to cover it as well as zones 6, 7 of the leading edge 2 and the trailing edge 3 contiguous to the core 4.
  • the faces of the core 4 not covered by the webs 5A, 5B forming free ends of the core 4 are here protected and reinforced by means of a mixture 22 of short fibers and resin inserted in a cavity defined by the sails 5A, 5B and the free edge of the core 4.
  • the leading edge 2 and the trailing edge 3 comprise extensions 10, 11, 12, 13 which protrude from the core 4 on each side of dawn 1.
  • FIG. 3 represents a first mode of attachment of the blade 1 to an annular casing 20 of a turbojet engine.
  • the housing 20 has orifices 26 for passage through the casing 20 of the extensions 10, 12 of the leading edge 2 and the trailing edge 3.
  • the orifices 26 are illustrated as being sufficiently extended to allow the extensions of the leading and trailing edges by the same orifice. However, it will be possible alternatively to make the orifices in two parts, including an upstream orifice and a downstream orifice for passing respectively the leading edge and the trailing edge.
  • the casing 20 is equipped with fastening means leading edges which comprise a peripheral rail 21 which extends around the casing, on a face thereof opposite the blade.
  • the rail 21 defines a housing adapted to receive the heads 24 of fasteners 23 in the general shape of T or L.
  • fasteners 23 in the general shape of T or L.
  • the fastener 23 has an opposite end 25 opposite the head 24 which is cut to accommodate the extension of the leading edge.
  • the fastening between the fastening element 23 and the extension 10 is here made by broaching.
  • the end 25 comprises an orifice, not visible here, located opposite the orifice 14 of the extension 10 of the leading edge 2, to receive a fixing pin 27.
  • Fixing the extension 12 of the trailing edge 3 is similarly performed by means of a second rail 21 ', in which a second fastening element 23' is engaged to cooperate with the extension 12 of the trailing edge 3, the any broach using a 27 'pin.
  • the rails 21, 21 'and the fixing elements 23, 23' are made by pultrusion and are impregnated with thermoplastic resin thus allowing the assembly to be joined together by a single operation of hot compaction to the casing. 20.
  • FIG. 3 represents, moreover, only one half of the blade 1.
  • the end portions 11, 13 which are not visible are fixed to an internal casing in such a way that identical to what has just been described.
  • the dawn may be fixed to only one of the housings.
  • FIG. 4 illustrates a second mode of attachment of the blade 1 to a turbojet casing 20.
  • the attachment means comprise a peripheral angle 30 extending around the housing.
  • the angle 30 extends on an opposite face of the housing 20 relative to the blade 1.
  • the housing 20 has through holes 26 allowing the extensions of the leading and trailing edges of the blade to pass through the housing 20 to extend facing the angle 30.
  • the angle 30 is made by pultrusion and is impregnated with thermoplastic resin.
  • the angle 30 has an L-shaped section, a first face 28 is here fixed to the housing 20 by hot compaction and a second face 29 is fixed to the extension 10 by broaching.
  • the face 29 of the angle 30 is pierced with an orifice coming opposite the orifice 114 formed in the extension 10 of the leading edge. It will be noted moreover that the orifice 114 is pierced perpendicularly to the orifice 14 of the previous embodiment. It will also be noted that the extension 10 has been machined to present an upright face bearing against the face facing the wing 29.
  • the different elements of the casing are joined together by thermocompaction.
  • the materials used for the production of the various elements 2, 3, 4, 5 of the blade 1 and the attachment means 21, 23, 27 can be composite materials as well as metallic materials or a combination both.
  • capping the free ends of the core 4 may be replaced or supplemented by a folding of the skin of one or more webs 5A, 5B.
  • the size of the webs 5A, 5B will be adjusted to provide a flap from covering the free end of the core.
  • attachment means of the housing and those of the leading edge and trailing edge can be secured to each other by hot compaction, welding, gluing or even using screw / nut torques or any other solution ensuring the maintenance of these elements between them.
  • the blades may have a different structure from that described and for example a monobloc structure.
  • FIGS. 3 and 4 suggest identical fixing means to each of the extensions 10, 11, 12, 13 of the leading edge 2 and the trailing edge 3 according to two different embodiments, it is not necessary to contrary to the invention that each extension is fixed to the casing 20 according to one or the other of the fixing means independently.
  • attachment means comprise an annular member in the form of a rail or a peripheral angle extending around the housing
  • attachment means could be envisaged, such as fixing lugs on which are fixed the ends of the blades after passing through the housing.

Landscapes

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

Abstract

The invention relates to a turbojet casing adapted to receive a plurality of blades and comprising means for attaching one end of each blade to the casing (21, 30). The invention is characterised in that the attachment means extend over a surface of the casing opposite the blades, and the casing comprises holes (26) for the passage of the ends of the blades, such that the latter can engage with the attachment means of the casing. The invention also relates to a turbojet comprising such a casing.

Description

Carter de turboréacteur et turboréacteur recevant de tels carters Turbojet engine casing and turbojet engine receiving such casings
La présente invention concerne un carter de turboréacteur adapté à recevoir une pluralité d'aubes ainsi qu'un turboréacteur intégrant de tels carters.  The present invention relates to a turbojet casing adapted to receive a plurality of blades and a turbojet incorporating such casings.
ARRIERE PLAN DE L'INVENTION  BACKGROUND OF THE INVENTION
On connaît des carters annulaires comportant des moyens d'accrochage destinés à coopérer avec les extrémités d'une aube.  Annular housings are known comprising attachment means intended to cooperate with the ends of a blade.
Différents moyens de d'accrochage ont été proposés. Par exemple, le document US2009/0317246 préconise des extrémités comportant une plateforme cylindrique formant une portion du carter externe et portant deux flancs de fixation, ce qui conduit à des formes complexes à fabriquer. Le document US2009/0317246 préconise la solidarisation des aubes entre elles au moyen d'un anneau circulaire avant de monter l'ensemble ainsi constitué dans le carter. C'est une solution lourde à mettre en œuvre, nécessitant des outillages d'assemblage.  Various attachment means have been proposed. For example, the document US2009 / 0317246 recommends ends having a cylindrical platform forming a portion of the outer casing and carrying two fixing flanks, which leads to complex shapes to manufacture. The document US2009 / 0317246 recommends the joining of the blades together by means of a circular ring before mounting the assembly thus formed in the housing. This is a cumbersome solution to implement, requiring assembly tools.
OBJET DE L'INVENTION  OBJECT OF THE INVENTION
Le but de l'invention est donc de proposer un carter pour turboréacteur simple à produire et facile à monter .  The object of the invention is therefore to provide a turbojet casing simple to produce and easy to assemble.
BREVE DESCRIPTION DE L'INVENTION BRIEF DESCRIPTION OF THE INVENTION
A cet effet, on propose un carter de turboréacteur adapté à recevoir une pluralité d'aubes, comportant des moyens d'accrochage d'une extrémité de chaque aube sur le carter. Selon l'invention, les moyens d'accrochage s'étendent sur une face du carter opposée aux aubes, le carter comporte des orifices pour laisser passer les extrémités des aubes de sorte qu'elles puissent coopérer avec les moyens d'accrochage du carter. For this purpose, there is provided a turbojet engine housing adapted to receive a plurality of blades, comprising means for hooking an end of each blade on the housing. According to the invention, the attachment means extend on one face of the housing opposite the blades, the casing has orifices for passing the ends of the blades so that they can cooperate with the attachment means of the housing.
Un tel agencement permet l'obtention d'un carter simple à produire et facile à monter.  Such an arrangement makes it possible to obtain a casing that is simple to produce and easy to assemble.
Selon un mode préféré de réalisation, les moyens d'accrochage comportent un membre annulaire s 'étendant autour du carter, le carter comportant des fibres longues et de la résine thermoplastique, et le membre annulaire étant obtenu par pultrusion et imprégné d'une résine thermoplastique soudable avec la résine thermoplastique du carter, l'ensemble étant assemblé par compaction à chaud. Ceci procure à l'ensemble une forte cohésion. According to a preferred embodiment, the means fastening means comprise an annular member extending around the casing, the casing comprising long fibers and thermoplastic resin, and the annular member being obtained by pultrusion and impregnated with a thermoplastic resin weldable with the thermoplastic resin of the housing, assembly being assembled by hot compaction. This gives the whole a strong cohesion.
L' invention concerne également un turboréacteur comprenant au moins un carter selon l'invention et une pluralité d'aubes ayant chacune une extrémité liée au carter .  The invention also relates to a turbojet comprising at least one housing according to the invention and a plurality of blades each having an end connected to the housing.
De préférence, dans ce turboréacteur, chacune des aubes comporte :  Preferably, in this turbojet engine, each blade comprises:
une portion avant monobloc allongée découpée dans un profilé pultrudé comportant des fibres liées par de la résine et formant bord d' attaque ;  an elongate, elongated front portion cut into a pultruded profile having resin bonded fibers and forming a leading edge;
une portion arrière monobloc allongée découpée dans un profilé pultrudé comportant des fibres liées par de la résine et formant bord de fuite ;  an elongated one-piece rear portion cut into a pultruded section comprising fibers bound by resin and forming a trailing edge;
une peau découpée dans un tissu de fibres imprégné de résine s' étendant pour recouvrir des faces latérales de l'âme et recouvrant au moins des zones du bord d'attaque et du bord de fuite contiguës à la portion centrale ;  skin cut from a resin-impregnated fiber fabric extending to cover side faces of the core and covering at least portions of the leading edge and the trailing edge adjacent to the central portion;
au moins l'un du bord d'attaque ou du bord de fuite présente des prolongements qui s'étendent en saillie de l'âme au moins d'un côté de l'aube, pour porter des moyens d'accrochage coopérant avec les moyens d'accrochage du carter du turboréacteur. at least one of the leading edge or the trailing edge has extensions which project from the web at least on one side of the blade, to carry hooking means cooperating with the means attachment of the turbojet casing.
BREVE DESCRIPTION DES DESSINS  BRIEF DESCRIPTION OF THE DRAWINGS
D'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la description qui suit de modes de réalisation particuliers de l'invention en relation avec les figures ci-jointes parmi lesquelles : Other characteristics and advantages of the invention will appear on reading the following description of particular embodiments of the invention. the invention in relation to the attached figures among which:
- la figure 1 est une vue de dessus d'une aube destinée à être fixée à un carter selon l'invention ;  - Figure 1 is a top view of a blade to be fixed to a housing according to the invention;
- la figure 2 est une vue en perspective de l'aube de la figure 1, la peau recouvrant l'âme de l'aube étant partiellement écorchée ;  - Figure 2 is a perspective view of the blade of Figure 1, the skin covering the soul of the blade being partially cut away;
la figure 3 est une vue en perspective d'un premier mode de fixation de l'aube à un carter selon l'invention ;  Figure 3 is a perspective view of a first mode of attachment of the blade to a housing according to the invention;
- la figure 4 est une vue en perspective d'un deuxième mode de fixation l'aube au carter selon 1 ' invention .  FIG. 4 is a perspective view of a second mode of fixing the blade to the casing according to the invention.
DESCRIPTION DETAILLEE DE L'INVENTION En référence aux figures 1 et 2, l'aube 1 qui est ici illustrée est une aube de redresseur, destinée à s'étendre derrière la soufflante d'un turboréacteur. L'aube 1 comprend un bord d'attaque 2 se présentant ici sous la forme d'une structure allongée monobloc. L'aube 1 comporte par ailleurs un bord de fuite 3 qui se présente également sous la forme d'une structure allongée monobloc .  DETAILED DESCRIPTION OF THE INVENTION Referring to Figures 1 and 2, the blade 1 which is illustrated here is a stator blade, intended to extend behind the fan of a turbojet engine. The blade 1 comprises a leading edge 2 which is here in the form of an elongate monobloc structure. The blade 1 further comprises a trailing edge 3 which is also in the form of an elongate monobloc structure.
Le bord d' attaque 2 et le bord de fuite 3 sont découpés dans des profilés obtenus par pultrusion, de préférence avec placement de fibres obliques (procédé dit "pullbraiding" ) . Les profilés comportent des fibres, par exemple des fibres de carbone, essentiellement disposées selon un axe longitudinal pour former un corps allongé. Idéalement, sensiblement 80% des fibres sont disposées selon l'axe longitudinal du bord d'attaque X et de fuite Y et 20% des fibres sont disposées selon une inclinaison d'environ 60 degrés par rapport à l'axe longitudinal. Ces proportions et l'agencement des fibres sont donnés à titre d'exemple. Les fibres sont ici imprégnées de résine thermoplastique. Entre le bord d' attaque 2 et le bord de fuite 3 s'étend une âme 4. Une peau 5 comportant ici deux voiles 5A, 5B obtenus par découpe dans un tissu de fibres pré¬ imprégné de résine thermoplastique, s'étendent de part et d'autre de l'âme 4 pour recouvrir celle-ci ainsi que des zones 6, 7 du bord d'attaque 2 et du bord de fuite 3 contigues à l'âme 4. The leading edge 2 and the trailing edge 3 are cut in profiles obtained by pultrusion, preferably with oblique fiber placement (so-called "pullbraiding" process). The profiles comprise fibers, for example carbon fibers, substantially disposed along a longitudinal axis to form an elongated body. Ideally, substantially 80% of the fibers are disposed along the longitudinal axis of the leading edge X and leakage Y and 20% of the fibers are disposed at an inclination of about 60 degrees to the longitudinal axis. These proportions and the arrangement of the fibers are given by way of example. The fibers are here impregnated with thermoplastic resin. Between the leading edge 2 and the trailing edge 3 extends a core 4. A skin 5 comprising here two webs 5A, 5B obtained by cutting in a fiber fabric pré ¬ impregnated with thermoplastic resin, extend from and other of the core 4 to cover it as well as zones 6, 7 of the leading edge 2 and the trailing edge 3 contiguous to the core 4.
Les faces de l'âme 4 non recouvertes par les voiles 5A, 5B formant des extrémités libres de l'âme 4 sont ici protégées et renforcées au moyen d'un mélange 22 de fibres courtes et de résine inséré dans une cavité définie par les voiles 5A, 5B et le bord libre de l'âme 4. Le bord d' attaque 2 et le bord de fuite 3 comportent des prolongements 10, 11, 12, 13 qui s'étendent en saillie de l'âme 4 de chaque côté de l'aube 1.  The faces of the core 4 not covered by the webs 5A, 5B forming free ends of the core 4 are here protected and reinforced by means of a mixture 22 of short fibers and resin inserted in a cavity defined by the sails 5A, 5B and the free edge of the core 4. The leading edge 2 and the trailing edge 3 comprise extensions 10, 11, 12, 13 which protrude from the core 4 on each side of dawn 1.
L'assemblage des différents composants de l'aube 1 entre eux est réalisé par compaction à chaud de manière à solidariser l'ensemble. Ce type d'assemblage confère une grande résistance à l'ensemble de l'aube 1.  The assembly of the various components of the blade 1 between them is made by hot compaction so as to secure the assembly. This type of assembly gives a great resistance to the whole of the dawn 1.
Enfin, on réalise dans les prolongements 10, 11, Finally, we realize in the extensions 10, 11,
12, 13 des orifices 14, 15, 16, 17 de sorte à transformer ces prolongements en moyens d'accrochage de l'aube 1 destinés à coopérer avec des moyens d' accrochage complémentaire d'un carter du turboréacteur, comme cela va maintenant être détaillé en relation avec les figures 3 et 4. 12, 13 of the orifices 14, 15, 16, 17 so as to transform these extensions into attachment means of the blade 1 intended to cooperate with means of complementary attachment of a turbojet engine housing, as will now be detailed in relation to FIGS. 3 and 4.
La figure 3 représente un premier mode de fixation de l'aube 1 à un carter annulaire 20 de turboréacteur. (On a représenté ici le carter externe du turboréacteur réalisé en fibre longues imprégnées de résine thermoplastique) . Le carter 20 comporte des orifices 26 pour le passage au travers du carter 20 des prolongements 10, 12 du bord d'attaque 2 et du bord de fuite 3. Les orifices 26 sont illustrés comme étant suffisamment étendus pour laisser passer les prolongements des bords d' attaque et de fuite par le même orifice. Cependant, on pourra en variante réaliser les orifices en deux parties, dont un orifice amont et un orifice aval pour laisser passer respectivement le bord d'attaque et le bord de fuite. FIG. 3 represents a first mode of attachment of the blade 1 to an annular casing 20 of a turbojet engine. (There is shown here the outer casing of the turbojet engine made of long fibers impregnated with thermoplastic resin). The housing 20 has orifices 26 for passage through the casing 20 of the extensions 10, 12 of the leading edge 2 and the trailing edge 3. The orifices 26 are illustrated as being sufficiently extended to allow the extensions of the leading and trailing edges by the same orifice. However, it will be possible alternatively to make the orifices in two parts, including an upstream orifice and a downstream orifice for passing respectively the leading edge and the trailing edge.
Le carter 20 est équipé de moyens d'accrochage des bords d'attaque qui comportent un rail 21 périphérique qui s'étend autour du carter, sur une face de celui-ci opposé à l'aube. Le rail 21 définit un logement apte à recevoir les têtes 24 d'éléments de fixation 23 en forme générale de T ou de L. Un de ces éléments est ici illustré.  The casing 20 is equipped with fastening means leading edges which comprise a peripheral rail 21 which extends around the casing, on a face thereof opposite the blade. The rail 21 defines a housing adapted to receive the heads 24 of fasteners 23 in the general shape of T or L. One of these elements is here illustrated.
L'élément de fixation 23 comporte une extrémité opposée 25 opposée à la tête 24 qui est découpée pour accueillir le prolongement 10 du bord d'attaque. La solidarisation entre l'élément de fixation 23 et le prolongement 10 est ici réalisée par brochage. A cet effet, l'extrémité 25 comporte un orifice, non visible ici, situé en regard de l'orifice 14 du prolongement 10 du bord d'attaque 2, pour recevoir une broche de fixation 27.  The fastener 23 has an opposite end 25 opposite the head 24 which is cut to accommodate the extension of the leading edge. The fastening between the fastening element 23 and the extension 10 is here made by broaching. For this purpose, the end 25 comprises an orifice, not visible here, located opposite the orifice 14 of the extension 10 of the leading edge 2, to receive a fixing pin 27.
La fixation du prolongement 12 du bord de fuite 3 est réalisée de manière similaire, au moyen d'un deuxième rail 21', dans lequel un deuxième élément de fixation 23' est engagé pour coopérer avec le prolongement 12 du bord de fuite 3, le tout broché à l'aide d'une broche 27' .  Fixing the extension 12 of the trailing edge 3 is similarly performed by means of a second rail 21 ', in which a second fastening element 23' is engaged to cooperate with the extension 12 of the trailing edge 3, the any broach using a 27 'pin.
Selon un mode de réalisation préféré, les rails 21, 21' et les éléments de fixation 23, 23' sont réalisés par pultrusion et sont imprégnés de résine thermoplastique permettant ainsi une solidarisation de l'ensemble par une opération unique de compaction à chaud au carter 20.  According to a preferred embodiment, the rails 21, 21 'and the fixing elements 23, 23' are made by pultrusion and are impregnated with thermoplastic resin thus allowing the assembly to be joined together by a single operation of hot compaction to the casing. 20.
La figure 3 ne représente, par ailleurs, qu'une moitié de l'aube 1. Ici les portions terminales 11, 13 non visibles sont fixées à un carter interne de façon identique à ce qui vient d'être décrit. Cependant, si l'aube n'a pas de fonction structurale, l'aube peut n'être fixée qu'à un seul des carters. FIG. 3 represents, moreover, only one half of the blade 1. Here the end portions 11, 13 which are not visible are fixed to an internal casing in such a way that identical to what has just been described. However, if the dawn has no structural function, the dawn may be fixed to only one of the housings.
La figure 4 illustre un deuxième mode de fixation de l'aube 1 à un carter 20 de turboréacteur. Ici, les moyens d'accrochage comportent une cornière 30 périphérique s' étendant autour du carter. La cornière 30 s'étend sur une face opposée du carter 20 par rapport à l'aube 1. Le carter 20 comporte des orifices de passage 26 permettant aux prolongements des bords d'attaque et de fuite de l'aube de traverser le carter 20 pour s'étendre en regard de la cornière 30.  FIG. 4 illustrates a second mode of attachment of the blade 1 to a turbojet casing 20. Here, the attachment means comprise a peripheral angle 30 extending around the housing. The angle 30 extends on an opposite face of the housing 20 relative to the blade 1. The housing 20 has through holes 26 allowing the extensions of the leading and trailing edges of the blade to pass through the housing 20 to extend facing the angle 30.
De manière préférentielle, la cornière 30 est réalisée par pultrusion et est imprégnée de résine thermoplastique.  Preferably, the angle 30 is made by pultrusion and is impregnated with thermoplastic resin.
La cornière 30 présente une section en L dont une première face 28 est ici fixée au carter 20 par compaction à chaud et une deuxième face 29 est fixée au prolongement 10 par brochage. A cet effet, la face 29 de la cornière 30 est percée d'un orifice venant en regard de l'orifice 114 pratiqué dans le prolongement 10 du bord d'attaque. On remarquera d'ailleurs que l'orifice 114 est percé perpendiculairement à l'orifice 14 du mode de réalisation précédent. On remarquera également que le prolongement 10 a été usiné pour présenter une face dressée venant en appui contre la face en regard de l'aile 29.  The angle 30 has an L-shaped section, a first face 28 is here fixed to the housing 20 by hot compaction and a second face 29 is fixed to the extension 10 by broaching. For this purpose, the face 29 of the angle 30 is pierced with an orifice coming opposite the orifice 114 formed in the extension 10 of the leading edge. It will be noted moreover that the orifice 114 is pierced perpendicularly to the orifice 14 of the previous embodiment. It will also be noted that the extension 10 has been machined to present an upright face bearing against the face facing the wing 29.
Comme dans l'exemple précédent, les différents éléments du carter sont solidarisés entre eux par thermocompaction .  As in the previous example, the different elements of the casing are joined together by thermocompaction.
Par ailleurs, les prolongements 11, 12, 13 du bord d'attaque 2 et du bord de fuite 3, non représentés, sont fixés de façon identique à une cornière similaire.  Furthermore, the extensions 11, 12, 13 of the leading edge 2 and the trailing edge 3, not shown, are fixed identically to a similar angle.
L'opération de fixation de l'aube 1 à la cornière 30 est répétée autant de fois que d'aubes sont à disposer . The operation of fixing the blade 1 to the angle 30 is repeated as many times as blades are at dispose.
Outre leur rôle pour la fixation des aubes par leur prolongement de bord d'attaque ou de bord de fuite, on remarquera que les rails et cornières contribuent également à rigidifier le carter du turboréacteur.  In addition to their role in fixing the vanes by their extension of leading edge or trailing edge, it will be noted that the rails and angles also contribute to stiffening the turbojet engine casing.
Bien entendu, l'invention n'est pas limitée aux modes de réalisation décrits ci-dessus et sont susceptibles de variantes qui apparaîtront à l'homme de métier sans sortir du cadre de l'invention tel que défini par les revendications.  Of course, the invention is not limited to the embodiments described above and are capable of variants that will occur to those skilled in the art without departing from the scope of the invention as defined by the claims.
Notamment, les matériaux utilisés pour la réalisation des différents éléments 2, 3, 4, 5 de l'aube 1 et des moyens d'accrochage 21, 23, 27 peuvent aussi bien être des matériaux composites que des matériaux métalliques ou d'une combinaison des deux.  In particular, the materials used for the production of the various elements 2, 3, 4, 5 of the blade 1 and the attachment means 21, 23, 27 can be composite materials as well as metallic materials or a combination both.
De même, les renforts 22, visibles à la figure 2, venant coiffer les extrémités libres de l'âme 4 peuvent être remplacés ou complétés par un rabattement de la peau d'un ou des voiles 5A, 5B . Dans ce cas, la dimension des voiles 5A, 5B sera ajustée pour prévoir un rabat venant recouvrir l'extrémité libre de l'âme.  Similarly, the reinforcements 22, visible in Figure 2, capping the free ends of the core 4 may be replaced or supplemented by a folding of the skin of one or more webs 5A, 5B. In this case, the size of the webs 5A, 5B will be adjusted to provide a flap from covering the free end of the core.
De même, les moyens d'accrochage du carter et ceux du bord d' attaque et de fuite peuvent être solidarisés entre eux par des opérations de compaction à chaud, de soudage, de collage ou encore utilisant des couples vis/écrou ou toute autre solution assurant le maintien de ces éléments entre eux.  Similarly, the attachment means of the housing and those of the leading edge and trailing edge can be secured to each other by hot compaction, welding, gluing or even using screw / nut torques or any other solution ensuring the maintenance of these elements between them.
En outre, les aubes peuvent avoir une structure différente de celle décrite et par exemple une structure monobloc.  In addition, the blades may have a different structure from that described and for example a monobloc structure.
Enfin, bien que les figures 3 et 4 suggèrent des moyens de fixation identiques à chacun des prolongements 10, 11, 12, 13 du bord d'attaque 2 et du bord de fuite 3 selon deux modes de réalisation différents, il n'est pas contraire à l'invention que chaque prolongement soit fixé au carter 20 selon l'un ou l'autre des moyens de fixation de manière indépendante. Finally, although FIGS. 3 and 4 suggest identical fixing means to each of the extensions 10, 11, 12, 13 of the leading edge 2 and the trailing edge 3 according to two different embodiments, it is not necessary to contrary to the invention that each extension is fixed to the casing 20 according to one or the other of the fixing means independently.
Bien qu'ici les moyens d'accrochage comportent un membre annulaire sous la forme d'un rail ou d'une cornière périphérique s ' étendant autour du carter, d'autres moyens d'accrochage pourraient être envisagés, comme des pattes de fixation sur lesquelles sont fixées les extrémités des aubes après traversée du carter.  Although here the attachment means comprise an annular member in the form of a rail or a peripheral angle extending around the housing, other attachment means could be envisaged, such as fixing lugs on which are fixed the ends of the blades after passing through the housing.

Claims

REVENDICATIONS
1. Carter de turboréacteur adapté à recevoir une pluralité d'aubes, comportant des moyens d'accrochage d'une extrémité de chaque aube sur le carter (21, 30), caractérisé en ce que les moyens d'accrochage s'étendent sur une face du carter opposée aux aubes, le carter comporte des orifices (26) pour laisser passer les extrémités des aubes de sorte qu'elles puissent coopérer avec les moyens d'accrochage du carter. A turbojet engine housing adapted to receive a plurality of blades, comprising means for hooking an end of each blade on the housing (21, 30), characterized in that the attachment means extend over a opposite to the housing opposite the blades, the housing has orifices (26) to allow the ends of the blades to pass so that they can cooperate with the attachment means of the housing.
2. Carter selon la revendication 1 dans lequel les moyens d'accrochage comportent un membre annulaire (21, 30) s ' étendant autour du carter.  2. The housing of claim 1 wherein the attachment means comprises an annular member (21, 30) extending around the housing.
3. Carter selon la revendication 2, dans lequel le membre annulaire comporte au moins un rail (21) périphérique dans lequel sont insérées des extrémités (24) d'éléments de fixation (23) des extrémités des aubes .  3. Carter according to claim 2, wherein the annular member comprises at least one rail (21) peripheral in which are inserted ends (24) of fasteners (23) of the ends of the blades.
4. Carter selon la revendication 2, dans lequel le membre annulaire comporte une cornière (30) périphérique sur laquelle sont directement fixées les extrémités des aubes.  4. Carter according to claim 2, wherein the annular member comprises a peripheral angle (30) on which are directly fixed the ends of the blades.
5. Carter selon la revendication 2, celui-ci étant réalisé en fibre longues associées à une résine thermoplastique, tandis que le membre annulaire (21, 30) est obtenu par pultrusion et imprégné d'une résine thermoplastique soudable avec la résine thermoplastique du carter, l'ensemble étant assemblé par compaction à chaud .  5. Carter according to claim 2, the latter being made of long fibers associated with a thermoplastic resin, while the annular member (21, 30) is obtained by pultrusion and impregnated with a thermoplastic resin weldable with the thermoplastic resin of the housing , the assembly being assembled by hot compaction.
6. Turboréacteur comprenant au moins un carter selon l'une des revendications précédentes, et une pluralité d'aubes ayant chacune une extrémité liée au carter .  6. Turbojet comprising at least one housing according to one of the preceding claims, and a plurality of blades each having an end connected to the housing.
7. Turboréacteur selon la revendication 6, dans lequel chacune des aubes comporte : une portion avant (2) monobloc allongée découpée dans un profilé pultrudé comportant des fibres liées par de la résine et formant bord d' attaque ; 7. Turbojet engine according to claim 6, wherein each blade comprises: an elongate, elongate, elongated front portion (2) cut into a pultruded section having resin bonded fibers and forming a leading edge;
une portion arrière (3) monobloc allongée découpée dans un profilé pultrudé comportant des fibres liées par de la résine et formant bord de fuite ;  an elongated one-piece rear portion (3) cut in a pultruded section comprising resin-bonded fibers forming a trailing edge;
une portion centrale (4) formant âme s' étendant entre le bord d'attaque (2) et le bord de fuite (3) ;  a central portion (4) forming a core extending between the leading edge (2) and the trailing edge (3);
une peau (5) découpée dans un tissu de fibres imprégné de résine s' étendant pour recouvrir des faces latérales de l'âme (4) et recouvrant au moins des zones (6, 7) du bord d'attaque (2) et du bord de fuite (3) contiguës à la portion centrale (4) ;  a skin (5) cut from a resin-impregnated fiber fabric extending to cover side faces of the web (4) and covering at least areas (6, 7) of the leading edge (2) and the trailing edge (3) contiguous to the central portion (4);
au moins l'un du bord d'attaque (2) ou du bord de fuite (3) présente des prolongements (10, 11, 12, 13) qui s'étendent en saillie de l'âme (4) au moins d'un côté de l'aube (1), pour porter des moyens d'accrochage (14, 15, 16, 17) de l'aube (1) coopérant avec les moyens d'accrochage du carter (20) du turboréacteur. at least one of the leading edge (2) or the trailing edge (3) has extensions (10, 11, 12, 13) which project from the web (4) at least one side of the blade (1), for carrying hooking means (14, 15, 16, 17) of the blade (1) cooperating with the fastening means of the housing (20) of the turbojet engine.
EP11754367.8A 2010-09-06 2011-09-05 Turbojet casing and turbojet receiving such casings Withdrawn EP2614258A1 (en)

Applications Claiming Priority (2)

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FR1057072A FR2964427B1 (en) 2010-09-06 2010-09-06 CARTRIDGE OF TURBOJET AND TURBOJET RECEIVING SUCH CARTERS
PCT/EP2011/065339 WO2012032017A1 (en) 2010-09-06 2011-09-05 Turbojet casing and turbojet receiving such casings

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BR (1) BR112013004717A2 (en)
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BR112013004717A2 (en) 2016-05-17
CA2810181A1 (en) 2012-03-15
FR2964427A1 (en) 2012-03-09
US20130251519A1 (en) 2013-09-26
RU2544107C2 (en) 2015-03-10
FR2964427B1 (en) 2014-05-09
WO2012032017A1 (en) 2012-03-15
RU2013115370A (en) 2014-10-20

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