EP3351736B1 - Stator-innenring eines kompressors eines axialen turbotriebwerks - Google Patents
Stator-innenring eines kompressors eines axialen turbotriebwerks Download PDFInfo
- Publication number
- EP3351736B1 EP3351736B1 EP18159641.2A EP18159641A EP3351736B1 EP 3351736 B1 EP3351736 B1 EP 3351736B1 EP 18159641 A EP18159641 A EP 18159641A EP 3351736 B1 EP3351736 B1 EP 3351736B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbomachine
- shroud
- rotor
- ferrule
- roughness
- 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.)
- Active
Links
- 239000000463 material Substances 0.000 description 6
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- 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
- 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
- F01D9/06—Fluid supply conduits to nozzles or the like
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- 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
-
- 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
Definitions
- the field of the present invention is that of axial turbomachines. More particularly, the invention addresses the internal ferrules connected to a row of stator vanes.
- An internal ferrule is known for making it possible to delimit the primary flow of an axial turbomachine, it forms an annular wall which delimits the interior of the fluid stream. Thanks to its external surface, it helps guide the flow during its expansion in a turbine, or its compression in a compressor.
- an internal ferrule can be mounted on the internal ends of vanes arranged in an annular row, themselves linked to an external casing.
- the ferrule has recesses for the introduction of the ferrule fixing ends.
- the internal ferrule is also intended to ensure a seal with the rotor around which it is placed. To this end, it has a layer of abradable material cooperating by abrasion with wipers formed outside the rotor. In operation, the wipers come close to the abradable, possibly creating circular notches there, so that a dynamic seal is ensured.
- each internal ferrule comprises a tubular wall in which are provided rows of openings. These allow the introduction of the blade roots used for fixing between the ferrule and the blades.
- Each opening has a lip which extends radially around it, ribs join the lips of the neighboring openings, the assembly making it possible to stiffen the ferrule.
- the bending stiffness of the shell; in particular of its segments remains limited.
- the main efforts are taken up by the branches of the U shape of the ferrule.
- the openings can open further around the seals surrounding the blades, which degrades the seal.
- the document EP1419849A1 discloses a method of repairing a turbine segment.
- the segment comprises a pair of blades, the ends of which are linked to an internal ferrule.
- the latter has two openings linked to the blades, the opposite edges of the openings being joined by a flange.
- the invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the sealing of a ferrule or a segment of a ferrule. The invention also aims to improve the rigidity of an assembly comprising a ferrule and vanes linked in openings formed in the ferrule. Another object of the invention is to stiffen an internal ferrule or an internal ferrule segment linked to stator vanes.
- the subject of the invention is a turbomachine comprising a rotor and an internal ferrule around the rotor or an internal ferrule segment matching the rotor, the ferrule or the ferrule segment comprising a circular or semi-circular wall whose profile mainly extends axially, and a circular or semi-circular radial flange extend radially from the wall towards the inside, the flange having a circular or semi-circular surface whose profile extends mainly radially, said surface having asperities.
- the rotor has annular ribs cooperating sealingly with the ferrule or the ferrule segment, the annular ribs of the rotor are each axially spaced from each radial flange of the ferrule or the ferrule segment. Furthermore, at least one or each radial flange comprises asperities which are formed over the majority of the radial height of the profile of revolution of one of the annular ribs of the rotor disposed opposite the associated radial flange.
- At least one or each radial flange comprises at least one surface with asperities, said surface being generally perpendicular to the axis of revolution of the ferrule or of the ferrule segment.
- the asperities form a pattern repeated on substantially an entire face of the corresponding radial flange.
- the radial flange makes it possible to form a bridge which spans each opening.
- the flange thus makes it possible to link the opposite edges of the openings so as to connect the edges.
- This mechanical seal makes it possible to link the opposite edges through each opening, so as to prevent them from moving apart or approaching despite the material vacuum of the openings.
- the invention makes it possible to improve the seal between a ferrule or a segment of a ferrule with openings in which stator vanes are fixed.
- the invention thus provides a ferrule or a segment of ferrule which is both light, rigid, and economical to produce.
- the terms internal or internal and external or external refer to a positioning relative to the axis of rotation of an axial turbomachine.
- the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
- the lateral direction is according to the circumference.
- the figure 1 represents in a simplified manner an axial turbomachine.
- the turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 5, a second level of compression, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
- a first level of compression called a low-pressure compressor 5
- a second level of compression called a high-pressure compressor 6
- a combustion chamber 8 and one or more levels of turbines 10.
- the mechanical power from the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 5 and 6.
- the latter comprise several rows of rotor blades associated with rows of stator blades.
- the rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8.
- Reduction means can increase the speed of rotation transmitted to the compressors.
- An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various above-mentioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the outlet of the turbine.
- the secondary flow can be accelerated so as to generate a thrust reaction.
- the primary 18 and secondary 20 flows are annular flows, they are channeled by the casing of the turbomachine.
- the casing has cylindrical or ferrule walls which can be internal and external.
- the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
- the compressor can be a low-pressure compressor 5.
- the rotor 12 comprises a drum with an external annular wall which supports several rows of rotor blades 24, in this case three rows.
- the low-pressure compressor 5 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26.
- the rectifiers are associated with the fan or with a row of rotor vanes to straighten the air flow, so as to convert the velocity of the flow into static pressure.
- the stator vanes 26 extend essentially radially from an external casing 22, and can be fixed to it using a pin.
- the casing 22 then forms an external support for the different rows.
- the compressor 5 also includes internal ferrules 28 which are fixed to the radially internal ends of the stator vanes 26.
- the internal ferrules 28 make it possible to guide and delimit the primary flow 18. They also provide a seal with the rotor 12 to avoid recirculation d air reducing the compression ratio of the compressor 5, and limiting the efficiency of the turbomachine.
- Each ferrule 28 can form a ring of a turn, or be segmented angularly.
- the figure 3 represents a portion of the compressor such as that of the figure 2 .
- the internal ferrule 28 could be segmented.
- the ferrule 28 has a profile of revolution with a portion extending mainly axially and which generates an axial wall 32.
- the axial wall 32 may be generally tubular, and be substantially inclined relative to the axis of rotation 14 of the turbomachine; the latter may coincide with the general axis of symmetry 14 of the shell 28.
- the ferrule 28 has a series of openings 34 arranged in an annular row. These openings 34 are crossed by the ends 30 of the vanes 26 to suspend the ferrule 28 there. Each opening 34 has opposite edges 36 in the direction of the row of openings 34, these edges 36 being placed opposite the faces of the associated dawn 26. One is facing the lower surface of the dawn, the other facing the upper surface.
- the edges 36 can generally be conjugates; one is concave, the other convex.
- the ferrule 28 further comprises at least one radial flange 38 which extends radially inwards from the axial wall 32.
- the ferrule 28 may comprise several radial flanges 38 which each cut the openings 34. These radial flanges may be parallel, and distributed axially through the openings.
- the ferrule 28 may comprise at least three radial flanges, including an upstream radial flange 40, a downstream radial flange 42, and a through radial flange 38 which passes through the openings 34, or central radial flange 38.
- the through radial flange 38 is disposed axially between the upstream 40 and downstream 42 flanges.
- the ferrule may have an “E” or comb profile.
- the rotor 12 in particular its wall has annular ribs 44, also called “wipers". They extend radially and cooperate with the shell 28 in a sealed manner. They can cooperate by abrasion with layers of abradable material 46 where they dig grooves in the event of contact.
- abradable material is meant a friable material in the event of contact.
- the abradable layers 46 can be applied to the ends of the blades 30, and / or to the axial wall 32.
- the abradable layers 46 and the radial flanges (38; 40; 42) form an alternation.
- the radial flanges (38; 40; 42) can be combined in pairs to frame each annular rib 44 of rotor 12, possibly individually.
- Each radial flange (38; 40; 42) comprises a profile of revolution which extends essentially radially, each flange profile extends over the majority of the radial height of each profile of the flange neighboring radial.
- Each rib profile (38; 40; 42) extends over the majority of the radial height of the profiles of the adjacent annular ribs 44.
- the faces of radial flanges (38; 40; 42) facing annular ribs 44 are covered with roughness 48 which amplifies turbulence 50, or vortices 50 opposing recirculations 52.
- the figure 4 represents a section of the ferrule 28 and the stator vanes 26 along the axis 4-4 traced on the figure 3 .
- the cutting plane passes through the radial flange 38 which crosses the openings 34.
- the ferrule could be formed by segments of ferrule which would be placed end to end so as to form a circle.
- the blades 26 extend radially from the ferrule 28 and pass through the openings 34. Their radial ends 30 are in radial abutment against the radial flange 38. Each blade end 30 has a radial abutment surface which cooperates with a abutment surface niche correspondent. Seals 54 extend radially into the openings 34 and pass through them, they come into contact with the radial flange 38. The bottoms of notches, or abutment surfaces of the notches, are spaced from the seals 54 and / or the axial wall.
- the radial flange 38 not only joins all the openings 34, but also connects all the opposite edges 36 to each other by crossing the openings 34. It forms a reinforcing bar which, in each opening 34, blocks the opposite edges 36
- the radial flange 38 has an arcuate shape and a notched profile. It comprises a series of steps forming notches 56 in which the ends 30 of the blades 30 are placed. These notches 56 can be a place for fixing the blades 26, for example by gluing or using fixing plates (not shown). To this end, the ends 30 may include fixing orifices (not shown). Within each opening 34, the radial flange 38 links the opposite edges 36. This configuration stiffens the ferrule 28, and prevents it from bending at the openings, 38 so that the risk of detachment at the joints 54 is reduced.
- the figure 5 represents a section along axis 5-5 drawn on the figure 3 .
- the section shows a compressor section between the rotor 12 and an internal shroud, seen from the outside. The location of the blade ends 30 is shown.
- the asperities 48 comprise grooves and ridges alternating with the grooves, They extend radially and are optionally perpendicular to the axis of rotation of the turbomachine.
- the assembly can form a striated annular surface.
- the asperities 48 may have triangular tooth shapes, and have a general sawtooth profile.
- the asperities 48 are formed opposite the wipers 44, preferably on each side.
- the pattern can be formed along, along the circumference, radial flanges (38; 40; 42); or all around. Thanks to the asperities 48, the radial flanges (38; 40; 42) cause vortices 50 in the air entrained by the rotor 12
- the figure 6 shows a diagram of a method of assembling a stator vane on a ferrule, the ferrule being able to be segmented.
- Step (b) supply 102 can comprise additive manufacturing of the shell or of the shell segment.
- the ferrule or each segment may have come from a mantle and be made of polymer, for example a composite martial material with fibers, possibly of length less than 10 mm.
- Positioning step (c) 104 can be carried out by fixing the blades to an external compressor casing. Then the ferrule is brought together radially so that the internal ends of the blades are found in the openings. Initially, the blade tips enter the openings, then pass through them. Finally, these ends abut against a radial flange. The stop is then axial and / or radial, which makes it possible to improve the relative position between the blade and the shell. Thus, the joint produced or implemented during step (e) implementation or production 108 is better positioned and / or better produced.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (9)
- Turbomaschine (2) mit einem Rotor (12) und einem um den Rotor (28) angeordneten inneren Klemmring (28) oder einem inneren Klemmringsegment, das an den Rotor (12) passt, wobei der Klemmring (28) oder das Klemmringsegment Folgendes umfasst:- eine kreisförmige oder halbkreisförmige Gehäusewand (32), deren Profil sich hauptsächlich axial erstreckt und- mindestens einen kreisförmigen oder halbkreisförmigen Radialflansch (38, 40, 42), der sich radial von der Gehäusewand (32) nach innen erstreckt und
dadurch gekennzeichnet ist, dass
der oder jeder Flansch (38, 40, 42) mindestens eine kreisförmige oder halbkreisförmige Oberfläche aufweist, deren Profil sich hauptsächlich radial erstreckt, wobei die Oberfläche Unebenheiten (48) aufweist,
dass der Rotor (12) ringförmige Rippen (44) aufweist, die abdichtend mit der Klemmring (28) oder dem Klemmringsegment zusammenwirken, wobei die ringförmigen Rippen (44) des Rotors (12) jeweils axial von jedem Radialflansch (38; 40; 42) des Klemmrings (28) oder dem Schalensegment entfernt sind,
und dass die Unebenheiten (48) auf der Mehrheit der radialen Höhe des Rotationsprofils einer der ringförmigen Rippen (44) des Rotors (12) geformt sind, die dem zugehörigen Radialflansch (38; 40; 42) gegenüberliegen. - Turbomaschine (2) nach Anspruch 1, dadurch gekennzeichnet, dass die Oberfläche des Flansches (38, 40, 42) mit den Unebenheiten (48) im Wesentlichen senkrecht zur Drehachse des Klemmrings (28) oder des Klemmringsegments steht.
- Turbomaschine (2) nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass die Unebenheiten (48) ein Muster bilden, das sich über im Wesentlichen über die ganze Fläche des entsprechenden Radialflansches (38, 40, 42) wiederholt.
- Turbomaschine (2) nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Unebenheiten (48) Nuten und Rippen umfassen, wobei sich die Rippen mit den Nuten abwechseln und sich radial erstrecken.
- Turbomaschine (2) nach Anspruch 4, dadurch gekennzeichnet, dass die Nuten und Grate senkrecht zur Drehachse (14) der Turbomaschine (2) stehen.
- Turbomaschine (2) nach einem der Ansprüche 4 oder 5, dadurch gekennzeichnet, dass alle Nuten und Grate eine ringförmige Rillenfläche bilden.
- Turbomaschine (2) nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Unebenheiten (48) Zahnformen aufweisen, die gegebenenfalls dreieckig sind, wobei sich jeder Zahn über die meiste oder gesamte Radialhöhe des zugehörigen Radialflansches (38, 40, 42) erstreckt.
- Turbomaschine (2) nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Unebenheiten (48) gegenüber den ringförmigen Rippen (44), vorzugsweise auf jeder Seite, ausgebildet sind.
- Turbomaschine (2) nach einem der Ansprüche 1 oder 8, dadurch gekennzeichnet, dass das Muster der Unebenheiten (48) entlang des Umfangs der Radialflansche (38; 40; 42) oder rund um die Flansche (38, 40, 42) vollständig ausgebildet ist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BE2014/0820A BE1022513B1 (fr) | 2014-11-18 | 2014-11-18 | Virole interne de compresseur de turbomachine axiale |
EP15190957.9A EP3023595B1 (de) | 2014-11-18 | 2015-10-22 | Stator-innenring eines kompressors eines axialen turbotriebwerks |
Related Parent Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15190957.9A Division EP3023595B1 (de) | 2014-11-18 | 2015-10-22 | Stator-innenring eines kompressors eines axialen turbotriebwerks |
EP15190957.9A Division-Into EP3023595B1 (de) | 2014-11-18 | 2015-10-22 | Stator-innenring eines kompressors eines axialen turbotriebwerks |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3351736A1 EP3351736A1 (de) | 2018-07-25 |
EP3351736B1 true EP3351736B1 (de) | 2020-01-29 |
Family
ID=52449883
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15190957.9A Active EP3023595B1 (de) | 2014-11-18 | 2015-10-22 | Stator-innenring eines kompressors eines axialen turbotriebwerks |
EP18159641.2A Active EP3351736B1 (de) | 2014-11-18 | 2015-10-22 | Stator-innenring eines kompressors eines axialen turbotriebwerks |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15190957.9A Active EP3023595B1 (de) | 2014-11-18 | 2015-10-22 | Stator-innenring eines kompressors eines axialen turbotriebwerks |
Country Status (6)
Country | Link |
---|---|
US (1) | US10113439B2 (de) |
EP (2) | EP3023595B1 (de) |
CN (1) | CN105604612B (de) |
BE (1) | BE1022513B1 (de) |
CA (1) | CA2909256A1 (de) |
RU (1) | RU2719521C2 (de) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3056684B1 (de) * | 2015-02-16 | 2018-05-16 | MTU Aero Engines GmbH | Axial geteilter Innenring für eine Strömungsmaschine, Leitschaufelkranz und Flugtriebwerk |
WO2016135973A1 (ja) * | 2015-02-27 | 2016-09-01 | 三菱重工業株式会社 | 過給機の製造方法 |
FR3045716B1 (fr) * | 2015-12-18 | 2018-01-26 | Safran Aircraft Engines | Ensemble d'anneau de turbine avec maintien elastique a froid |
BE1025283B1 (fr) | 2017-06-02 | 2019-01-11 | Safran Aero Boosters S.A. | Systeme d'etancheite pour compresseur de turbomachine |
DE102017211316A1 (de) | 2017-07-04 | 2019-01-10 | MTU Aero Engines AG | Turbomaschinen-Dichtring |
FR3085993B1 (fr) * | 2018-09-17 | 2020-12-25 | Safran Aircraft Engines | Aube mobile pour une roue d'une turbomachine |
FR3087825B1 (fr) * | 2018-10-29 | 2020-10-30 | Safran Aircraft Engines | Secteur d'anneau de turbine a languettes d'etancheite refroidies |
FR3088671B1 (fr) * | 2018-11-16 | 2021-01-29 | Safran Aircraft Engines | Etancheite entre une roue mobile et un distributeur d'une turbomachine |
FR3091725B1 (fr) | 2019-01-14 | 2022-07-15 | Safran Aircraft Engines | Ensemble pour une turbomachine |
US10822987B1 (en) | 2019-04-16 | 2020-11-03 | Pratt & Whitney Canada Corp. | Turbine stator outer shroud cooling fins |
JP7370226B2 (ja) * | 2019-11-19 | 2023-10-27 | 三菱重工業株式会社 | 蒸気タービン |
FR3103851B1 (fr) * | 2019-12-03 | 2021-11-05 | Safran Aircraft Engines | Barre rigide pour le raccordement electrique d’une machine dans une turbomachine d’aeronef |
Family Cites Families (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2410588A (en) * | 1942-06-23 | 1946-11-05 | Northrop Aircraft Inc | Turbine blade and assembly thereof |
US2771622A (en) * | 1952-05-09 | 1956-11-27 | Westinghouse Electric Corp | Diaphragm apparatus |
US2962809A (en) * | 1953-02-26 | 1960-12-06 | Gen Motors Corp | Method of making a compressor seal |
US3836282A (en) * | 1973-03-28 | 1974-09-17 | United Aircraft Corp | Stator vane support and construction thereof |
FR2452590A1 (fr) * | 1979-03-27 | 1980-10-24 | Snecma | Garniture d'etancheite amovible pour segment de distributeur de turbomachine |
US4710097A (en) * | 1986-05-27 | 1987-12-01 | Avco Corporation | Stator assembly for gas turbine engine |
US5201847A (en) * | 1991-11-21 | 1993-04-13 | Westinghouse Electric Corp. | Shroud design |
US5722813A (en) * | 1996-10-28 | 1998-03-03 | Alliedsignal Inc. | Segmented composite compressor deswirl |
US6409472B1 (en) * | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
US6543995B1 (en) * | 1999-08-09 | 2003-04-08 | United Technologies Corporation | Stator vane and stator assembly for a rotary machine |
US6494677B1 (en) * | 2001-01-29 | 2002-12-17 | General Electric Company | Turbine nozzle segment and method of repairing same |
FR2833035B1 (fr) * | 2001-12-05 | 2004-08-06 | Snecma Moteurs | Plate-forme d'aube de distributeur pour moteur a turbine a gaz |
US6793457B2 (en) * | 2002-11-15 | 2004-09-21 | General Electric Company | Fabricated repair of cast nozzle |
FR2856749B1 (fr) * | 2003-06-30 | 2005-09-23 | Snecma Moteurs | Redresseur de compresseur de moteur aeronautique a aubes collees |
US7229245B2 (en) * | 2004-07-14 | 2007-06-12 | Power Systems Mfg., Llc | Vane platform rail configuration for reduced airfoil stress |
GB2427900B (en) * | 2005-07-02 | 2007-10-10 | Rolls Royce Plc | Vane support in a gas turbine engine |
US7530782B2 (en) * | 2005-09-12 | 2009-05-12 | Pratt & Whitney Canada Corp. | Foreign object damage resistant vane assembly |
EP2075414A1 (de) | 2007-12-27 | 2009-07-01 | Techspace aero | Stator-Innenring für die Begrenzung des Primärflusses des Triebwerks eines Luftfahrzeugs |
EP2196629B1 (de) * | 2008-12-11 | 2018-05-16 | Safran Aero Boosters SA | Segmentierter Verbundmantelring eines axialen Verdichters |
US8544173B2 (en) * | 2010-08-30 | 2013-10-01 | General Electric Company | Turbine nozzle biform repair |
US8966756B2 (en) * | 2011-01-20 | 2015-03-03 | United Technologies Corporation | Gas turbine engine stator vane assembly |
EP2746538B1 (de) * | 2012-12-24 | 2016-05-18 | Techspace Aero S.A. | Befestigungsplatte einer Statorschaufel eines Turbotriebwerks mit internen Ausparungen |
-
2014
- 2014-11-18 BE BE2014/0820A patent/BE1022513B1/fr not_active IP Right Cessation
-
2015
- 2015-10-22 CA CA2909256A patent/CA2909256A1/en not_active Abandoned
- 2015-10-22 EP EP15190957.9A patent/EP3023595B1/de active Active
- 2015-10-22 EP EP18159641.2A patent/EP3351736B1/de active Active
- 2015-10-27 US US14/923,483 patent/US10113439B2/en active Active
- 2015-10-27 RU RU2015146074A patent/RU2719521C2/ru active
- 2015-10-30 CN CN201510727847.4A patent/CN105604612B/zh active Active
Non-Patent Citations (1)
Title |
---|
None * |
Also Published As
Publication number | Publication date |
---|---|
RU2015146074A (ru) | 2017-05-16 |
RU2719521C2 (ru) | 2020-04-21 |
US10113439B2 (en) | 2018-10-30 |
EP3023595A1 (de) | 2016-05-25 |
US20160138413A1 (en) | 2016-05-19 |
RU2015146074A3 (de) | 2019-05-20 |
CN105604612A (zh) | 2016-05-25 |
CA2909256A1 (en) | 2016-05-18 |
EP3351736A1 (de) | 2018-07-25 |
CN105604612B (zh) | 2018-08-28 |
BE1022513B1 (fr) | 2016-05-19 |
EP3023595B1 (de) | 2018-04-18 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3351736B1 (de) | Stator-innenring eines kompressors eines axialen turbotriebwerks | |
EP3018295B1 (de) | Gemischter kompressorstator eines axialen turbotriebwerks | |
EP2977549B1 (de) | Beschaufelung einer axialen strömungsmaschine und zugehörige turbomachine | |
EP2799721B1 (de) | LEITSCHAUFELANORDNUNG EINER AXIALEN TURBOMASCHINE MIT HILFSFLÜGELN AN DEN LAUFRADSCHAUFELSFÜßEN | |
EP2735707B1 (de) | Leitrad einer axialen Turbomaschine mit segmentiertem Innendeckband und zugehöriger Verdichter | |
EP3273003B1 (de) | Leitschaufelsegment eines verdichters eines axialen turbotriebwerks | |
BE1022809B1 (fr) | Aube composite de compresseur de turbomachine axiale | |
EP2735706B1 (de) | Gleichrichter mit Laufradschaufeln eines Kompressors eines axialen Turbotriebwerks, und Herstellungsverfahren | |
EP2977559B1 (de) | Stator einer axialen strömungsmaschine und zugehörige strömungsmaschine | |
EP2937517A1 (de) | Stator einer axialen Turbomachine und zugehörige Turbomachine | |
EP3095963B1 (de) | Laufradschaufel und deckband eines kompressors eines axialen turbotriebwerks | |
EP2873810B2 (de) | Ringförmiger Deckel zur Begrenzung der Lagerkammer eines Turbotriebwerks | |
BE1022364B1 (fr) | Compresseur de turbomachine axiale avec double rotors contrarotatifs | |
EP2886804B1 (de) | Dichtungsanordnung für einen Verdicther eines Turbotriebwerks | |
EP2977548B1 (de) | Schaufel und zugehörige strömungsmaschine | |
EP2843196B1 (de) | Verdichter einer turbomaschine und zugehörige turbomaschine | |
EP2818635B1 (de) | Kompressortrommel einer axialen Turbomaschine mit gemischter Befestigung der Laufradschaufeln | |
EP2937516B1 (de) | Rundgebogenes Monoblock-Gehäuse für Kompressor einer axialen Turbomaschine und entsprechendes Fertigungsverfahren | |
EP2886802B1 (de) | Innenringdichtung der letzten Kompressorstufe eines axialen Turbotriebwerks | |
EP2762681B1 (de) | Rotortrommel einer axialen Turbomaschine und zugehörige Turbomaschine | |
EP2458157B1 (de) | Abriebdichtung eines Stator-Innenrings | |
BE1025092B1 (fr) | Joint a brosse pour rotor de turbomachine | |
BE1023367B1 (fr) | Fixation de virole interne de compresseur de turbomachine axiale | |
EP2977550A1 (de) | Verdichterschaufel einer axialen Strömungsmaschine mit Verzweigungen an dem inneren und äusseren Ende |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED |
|
AC | Divisional application: reference to earlier application |
Ref document number: 3023595 Country of ref document: EP Kind code of ref document: P |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20190121 |
|
RBV | Designated contracting states (corrected) |
Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F01D 9/04 20060101AFI20190708BHEP Ipc: F01D 11/00 20060101ALI20190708BHEP |
|
INTG | Intention to grant announced |
Effective date: 20190806 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AC | Divisional application: reference to earlier application |
Ref document number: 3023595 Country of ref document: EP Kind code of ref document: P |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 1228636 Country of ref document: AT Kind code of ref document: T Effective date: 20200215 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: FRENCH |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602015046338 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20200129 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200621 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200429 Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200430 Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200429 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200529 Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602015046338 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1228636 Country of ref document: AT Kind code of ref document: T Effective date: 20200129 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20201030 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201022 Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201031 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20201022 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: MT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 Ref country code: AL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200129 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20230920 Year of fee payment: 9 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20240919 Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: BE Payment date: 20240919 Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20240919 Year of fee payment: 10 |