FR3128249A1 - Assembly of a bladed turbomachine fan - Google Patents
Assembly of a bladed turbomachine fan Download PDFInfo
- Publication number
- FR3128249A1 FR3128249A1 FR2110932A FR2110932A FR3128249A1 FR 3128249 A1 FR3128249 A1 FR 3128249A1 FR 2110932 A FR2110932 A FR 2110932A FR 2110932 A FR2110932 A FR 2110932A FR 3128249 A1 FR3128249 A1 FR 3128249A1
- Authority
- FR
- France
- Prior art keywords
- clutch means
- shroud
- low pressure
- dog clutch
- assembly according
- 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.)
- Pending
Links
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
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- 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
- F05D2240/60—Shafts
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- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/184—Two-dimensional patterned sinusoidal
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/31—Retaining bolts or nuts
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/02—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for connecting two abutting shafts or the like
- F16D1/033—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for connecting two abutting shafts or the like by clamping together two faces perpendicular to the axis of rotation, e.g. with bolted flanges
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/06—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end
- F16D1/076—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end by clamping together two faces perpendicular to the axis of rotation, e.g. with bolted flanges
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/10—Quick-acting couplings in which the parts are connected by simply bringing them together axially
- F16D1/101—Quick-acting couplings in which the parts are connected by simply bringing them together axially without axial retaining means rotating with the coupling
Abstract
Le présent document concerne un assemblage pour turbomachine comprenant un disque de soufflante (102) rotatif autour d’un axe longitudinal et un arbre basse pression (110) apte à entrainer un rotor de compresseur basse pression autour de l’axe longitudinal, dans lequel le disque de soufflante comprend une virole (106) s’étendant le long de l’axe longitudinal et configurée pour être emmanchée autour de l’arbre basse pression, une extrémité longitudinale de ladite virole comprenant des premiers moyens de crabotage prévus dans un épaulement de ladite virole (106) et l’arbre basse pression (110) comprend des seconds moyens de crabotage (118) prévus dans un épaulement (120) de l’arbre pression, les seconds moyens de crabotage (120) étant en prise avec les premiers moyens de crabotages. Figure à publier avec l’abrégé : [Fig. 2]This document relates to an assembly for a turbomachine comprising a fan disc (102) rotatable around a longitudinal axis and a low pressure shaft (110) capable of driving a low pressure compressor rotor around the longitudinal axis, in which the fan disc comprises a shroud (106) extending along the longitudinal axis and configured to be fitted around the low pressure shaft, a longitudinal end of said shroud comprising first clutch means provided in a shoulder of said ferrule (106) and the low pressure shaft (110) comprises second dog clutch means (118) provided in a shoulder (120) of the pressure shaft, the second dog clutch means (120) being engaged with the first means of dogfights. Figure to be published with abstract: [Fig. 2]
Description
Domaine technique de l’inventionTechnical field of the invention
La présente invention est relative à un assemblage sur un arbre de turbomachine d'au moins un disque aubagé par exemple de soufflante et d'un arbre relié à un compresseur basse pression.The present invention relates to an assembly on a turbomachine shaft of at least one bladed disc, for example of a fan, and a shaft connected to a low-pressure compressor.
Etat de la technique antérieureState of the prior art
Classiquement, le disque aubagé de la soufflante d'une turbomachine et le rotor de son compresseur basse pression sont fixés sur l'arbre du compresseur basse pression par différents systèmes de brides. Cet assemblage est configuré pour transmettre la rotation de la soufflante au rotor du compresseur basse pression.Conventionally, the bladed disc of the fan of a turbomachine and the rotor of its low-pressure compressor are fixed to the shaft of the low-pressure compressor by various flange systems. This assembly is configured to transmit the rotation of the fan to the rotor of the low pressure compressor.
Par exemple, le document FR3066552 décrit une turbomachine, dont la partie amont est représentée sur la
Le flasque de fixation 6 se termine par une virole cylindrique 8 à cannelures qui est engagée sur une zone 9 de la partie amont de l'arbre 3 qui comporte des cannelures complémentaires.The fixing flange 6 ends in a cylindrical ferrule 8 with splines which is engaged on a zone 9 of the upstream part of the shaft 3 which comprises complementary splines.
Les cannelures de la virole 8 qui termine le flasque de fixation 6 du disque aubagé et celles de la zone 9 de l'arbre 3 coopèrent pour assurer la liaison en rotation du disque aubagé 1 et de l'arbre basse pression 3. Le rotor 2 du compresseur basse pression comporte un flasque amont 10 qui définit un disque de rotor et qui porte plusieurs étages d'aubes mobiles 11.The splines of the shroud 8 which terminates the fixing flange 6 of the bladed disc and those of the zone 9 of the shaft 3 cooperate to ensure the connection in rotation of the bladed disc 1 and the low pressure shaft 3. The rotor 2 of the low-pressure compressor comprises an upstream flange 10 which defines a rotor disc and which carries several stages of moving blades 11.
Le compresseur basse pression comporte en outre plusieurs étages d'aubes 12 de redresseur. Les différents étages d'aubes de redresseur 12 et d'aubes mobiles 11 sont disposés à la suite les uns des autres, en alternance, pour définir ledit compresseur basse pression.The low-pressure compressor further comprises several stages of stator vanes 12. The different stages of stator vanes 12 and moving vanes 11 are arranged one after the other, alternately, to define said low-pressure compressor.
Ce flasque 10 se termine au niveau de l'arbre 3 par une virole de fixation cylindrique 13 à cannelures engagée sur une deuxième zone 14 à cannelures que ledit arbre basse pression 3 présente en amont de la zone 9.This flange 10 ends at the level of the shaft 3 by a cylindrical fastening ring 13 with splines engaged on a second zone 14 with splines that said low-pressure shaft 3 has upstream of zone 9.
Les cannelures du cylindre 13 et celles de la zone 14 coopèrent pour assurer une liaison cannelée qui bloque en en rotation relative le rotor 2 et l'arbre basse pression 3.The splines of the cylinder 13 and those of the zone 14 cooperate to ensure a splined connection which blocks in relative rotation the rotor 2 and the low pressure shaft 3.
Cette liaison à cannelures nécessite l’usinage de deux centrages 15 et 17 pour assurer la coaxialité entre le disque aubagé 1 et le compresseur basse pression.This spline connection requires the machining of two centerings 15 and 17 to ensure coaxiality between the bladed disc 1 and the low pressure compressor.
Les centrages 15 et 17 sont soumis à une cotation complexe à réaliser en fabrication. De plus, l’opération de taillage des cannelures est complexe et coûteuse. Enfin, cette liaison par cannelures est une zone critique pour la durée de vie de la turbomachine.Centerings 15 and 17 are subject to a complex dimensioning to be carried out during manufacture. In addition, the spline cutting operation is complex and expensive. Finally, this spline connection is a critical zone for the life of the turbomachine.
Le présent document vise à remédier à ces inconvénients.This document aims to remedy these drawbacks.
A cet effet, le présent document propose un assemblage pour turbomachine comprenant un disque de soufflante rotatif autour d’un axe longitudinal et un arbre basse pression apte à entrainer un rotor de compresseur basse pression autour de l’axe longitudinal, dans lequel le disque de soufflante comprend une virole s’étendant le long de l’axe longitudinal et configurée pour être emmanchée autour de l’arbre basse pression, une extrémité longitudinale de ladite virole comprenant des premiers moyens de crabotage prévus dans un épaulement de ladite virole et l’arbre basse pression comprend des seconds moyens de crabotage prévus dans un épaulement de l’arbre pression, les seconds moyens de crabotage étant en prise avec les premiers moyens de crabotages.To this end, the present document proposes an assembly for a turbomachine comprising a fan disc rotating around a longitudinal axis and a low-pressure shaft able to drive a low-pressure compressor rotor around the longitudinal axis, in which the fan disc fan comprises a shroud extending along the longitudinal axis and configured to be fitted around the low pressure shaft, a longitudinal end of said shroud comprising first dog clutch means provided in a shoulder of said shroud and the shaft low pressure comprises second dog clutch means provided in a shoulder of the pressure shaft, the second dog clutch means being engaged with the first dog clutch means.
Un tel assemblage par crabotage permet de simplifier l’usinage du disque de la soufflante et du rotor de compresseur basse pression. En outre, cet assemblage permet d’augmenter la durée de vie de la turbomachine.Such an assembly by dog clutching makes it possible to simplify the machining of the fan disc and the low pressure compressor rotor. In addition, this assembly increases the service life of the turbomachine.
La virole du disque de soufflante peut comprendre les premiers moyens de crabotage au niveau de son extrémité aval. Alternativement, la virole du disque de soufflante peut comprendre les premiers moyens de crabotage au niveau de son extrémité amont.The shroud of the fan disc may include the first dog clutch means at its downstream end. Alternatively, the shroud of the fan disc may include the first dog clutch means at its upstream end.
L’amont et l’aval sont définis en fonction de la circulation de l’air dans la turbomachine.Upstream and downstream are defined according to the air circulation in the turbomachine.
Le compresseur basse pression peut être agencé en aval de la soufflante.The low pressure compressor can be arranged downstream of the fan.
L’assemblage peut comprendre un organe de serrage apte à être monté sur l’arbre basse pression en amont de la virole du disque de soufflante et venir longitudinalement en butée contre ladite virole pour bloquer axialement le disque de soufflante par rapport à l’arbre basse pression.The assembly may comprise a clamping member adapted to be mounted on the low-pressure shaft upstream of the shroud of the fan disk and come longitudinally into abutment against said shroud to axially block the fan disk with respect to the low shaft pressure.
Selon un mode de réalisation, les premiers moyens de crabotage et les seconds moyens de crabotage peuvent présenter un profil rectangulaire.According to one embodiment, the first dog clutch means and the second dog clutch means may have a rectangular profile.
Selon un mode de réalisation, les premiers moyens de crabotage et les seconds moyens de crabotage peuvent présenter un profil sinusoïdal.According to one embodiment, the first dog clutch means and the second dog clutch means may have a sinusoidal profile.
L’épaisseur des premiers moyens de crabotage, suivant la direction radiale, peut être inférieure à l’épaisseur total de la virole, suivant la direction radiale.The thickness of the first dog clutch means, in the radial direction, may be less than the total thickness of the shroud, in the radial direction.
Les premiers moyens de crabotage et les seconds moyens de crabotage peuvent être formés par des rainures aménagées dans l’épaulement de la virole, respectivement dans l’épaule de l’arbre basse pression.The first dog clutch means and the second dog clutch means can be formed by grooves arranged in the shoulder of the ferrule, respectively in the shoulder of the low pressure shaft.
L’assemblage peut comprendre un palier de guidage dans lequel est monté l’arbre basse pression. La virole du disque de soufflante peut être longitudinalement en butée contre ledit palier de guidage.The assembly may include a guide bearing in which the low pressure shaft is mounted. The shroud of the fan disk can abut longitudinally against said guide bearing.
Par exemple, le palier de guidage peut comprendre une bague interne montée serrée autour de l’arbre basse pression, ladite virole du disque de soufflante étant en butée contre la bague interne du palier de guidage.For example, the guide bearing may comprise an inner race tightly fitted around the low pressure shaft, said shroud of the fan disk being in abutment against the inner race of the guide bearing.
L’assemblage peut comprendre des moyens d’étanchéité comprenant un flasque d’étanchéité et une cage d’étanchéité. Ledit flasque d’étanchéité peut comprendre une première partie d’extrémité formant un joint dynamique avec une partie correspondante de la virole du disque de soufflante et une seconde partie d’extrémité formant une retenue d’une partie élastiquement déformable de la cage d’étanchéité laquelle peut être reliée à une bague externe du palier de guidage en rotation de l’arbre basse pression.The assembly may include sealing means comprising a sealing flange and a sealing cage. Said sealing flange may comprise a first end part forming a dynamic seal with a corresponding part of the shroud of the fan disk and a second end part forming a retainer for an elastically deformable part of the sealing cage which can be connected to an outer ring of the rotational guide bearing of the low pressure shaft.
Les moyens d’étanchéité peuvent être agencés en aval de la virole du disque de soufflante. La virole du disque de soufflante peut comprendre des léchettes d’abradable sur une surface radialement externe de ladite virole du disque de soufflante. La première partie d’extrémité du flasque d’étanchéité peut reposer sur lesdites léchettes d’abradable.The sealing means can be arranged downstream of the shroud of the fan disk. The fan disk shroud may include abradable wipers on a radially outer surface of said fan disk shroud. The first end portion of the sealing flange can rest on said abradable wipers.
Le rotor de compresseur basse pression peut comprendre au moins deux étages d’aubes mobiles alternés avec des étages d’aubes de stator.The low pressure compressor rotor may comprise at least two stages of moving blades alternated with stages of stator vanes.
Le flasque d’étanchéité peut être agencé en amont de la cage d’étanchéité et la seconde extrémité du flasque d’étanchéité peut être agencée radialement à l’extérieur de la première extrémité du flasque d’étanchéité.The sealing flange can be arranged upstream of the sealing cage and the second end of the sealing flange can be arranged radially outside the first end of the sealing flange.
Le disque de soufflante peut comprendre une virole radialement externe par rapport à la virole comprenant les premiers moyens de crabotage et un moyeu reliant la virole radialement externe à ladite virole comprenant les premiers moyens de crabotage.The fan disc may comprise a shroud radially external with respect to the shroud comprising the first dog clutch means and a hub connecting the radially outer shroud to said shroud comprising the first dog clutch means.
Le présent document concerne en outre une turbomachine un assemblage tel que précité.This document also relates to a turbomachine, an assembly as mentioned above.
Brève description des figuresBrief description of figures
Claims (10)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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FR2110932A FR3128249A1 (en) | 2021-10-14 | 2021-10-14 | Assembly of a bladed turbomachine fan |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2110932A FR3128249A1 (en) | 2021-10-14 | 2021-10-14 | Assembly of a bladed turbomachine fan |
FR2110932 | 2021-10-14 |
Publications (1)
Publication Number | Publication Date |
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FR3128249A1 true FR3128249A1 (en) | 2023-04-21 |
Family
ID=79601865
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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FR2110932A Pending FR3128249A1 (en) | 2021-10-14 | 2021-10-14 | Assembly of a bladed turbomachine fan |
Country Status (1)
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FR (1) | FR3128249A1 (en) |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150377027A1 (en) * | 2014-05-19 | 2015-12-31 | Rolls-Royce Plc | Fan disc |
US9353626B2 (en) * | 2012-09-13 | 2016-05-31 | Pratt & Whitney Canada Corp. | Rotor assembly |
FR3066552A1 (en) | 2017-05-22 | 2018-11-23 | Safran Aircraft Engines | ASSEMBLY ON A TURBOMACHINE SHAFT OF A MONOBLOCK AUBING DISC AND A LOW PRESSURE COMPRESSOR ROTOR WITH AT LEAST TWO FLOORS OF MOBILE AUBES |
US20190048887A1 (en) * | 2017-08-09 | 2019-02-14 | Rolls-Royce Plc | Fan disc apparatus |
US20190218921A1 (en) * | 2018-01-12 | 2019-07-18 | Rolls-Royce Plc | Fan disc assembly |
-
2021
- 2021-10-14 FR FR2110932A patent/FR3128249A1/en active Pending
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9353626B2 (en) * | 2012-09-13 | 2016-05-31 | Pratt & Whitney Canada Corp. | Rotor assembly |
US20150377027A1 (en) * | 2014-05-19 | 2015-12-31 | Rolls-Royce Plc | Fan disc |
FR3066552A1 (en) | 2017-05-22 | 2018-11-23 | Safran Aircraft Engines | ASSEMBLY ON A TURBOMACHINE SHAFT OF A MONOBLOCK AUBING DISC AND A LOW PRESSURE COMPRESSOR ROTOR WITH AT LEAST TWO FLOORS OF MOBILE AUBES |
US20190048887A1 (en) * | 2017-08-09 | 2019-02-14 | Rolls-Royce Plc | Fan disc apparatus |
US20190218921A1 (en) * | 2018-01-12 | 2019-07-18 | Rolls-Royce Plc | Fan disc assembly |
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