WO2012114029A1 - Arbre d'entrainement de boitier a engrenages de machines auxiliaires d'un turboreacteur - Google Patents
Arbre d'entrainement de boitier a engrenages de machines auxiliaires d'un turboreacteur Download PDFInfo
- Publication number
- WO2012114029A1 WO2012114029A1 PCT/FR2012/050354 FR2012050354W WO2012114029A1 WO 2012114029 A1 WO2012114029 A1 WO 2012114029A1 FR 2012050354 W FR2012050354 W FR 2012050354W WO 2012114029 A1 WO2012114029 A1 WO 2012114029A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- shaft
- turbojet engine
- bearings
- drive shaft
- bearing
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60K—ARRANGEMENT OR MOUNTING OF PROPULSION UNITS OR OF TRANSMISSIONS IN VEHICLES; ARRANGEMENT OR MOUNTING OF PLURAL DIVERSE PRIME-MOVERS IN VEHICLES; AUXILIARY DRIVES FOR VEHICLES; INSTRUMENTATION OR DASHBOARDS FOR VEHICLES; ARRANGEMENTS IN CONNECTION WITH COOLING, AIR INTAKE, GAS EXHAUST OR FUEL SUPPLY OF PROPULSION UNITS IN VEHICLES
- B60K25/00—Auxiliary drives
- B60K25/06—Auxiliary drives from the transmission power take-off
-
- 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
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- 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
-
- 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
-
- 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
- F05D2220/50—Application for auxiliary power units (APU's)
Definitions
- the present invention relates to the field of multi-body and multi-stream aircraft turbojet engines. It aims at a specific configuration of a drive shaft in a radial arm of an intermediate casing of such a turbojet engine.
- a double-body turbojet engine comprises two coaxial shafts, one said to be low pressure or LP, connecting the low pressure compressor to the low pressure turbine and forming the BP body together, the other, said high pressure or HP, connecting the compressor high pressure to the high pressure turbine and together forming the HP body.
- the transmission of power to the auxiliaries is generally provided by a radial shaft, housed in an arm of the intermediate casing, one end of which comprises a conical pinion cooperating with a pinion integral with the high pressure body.
- the other end is mechanically connected to a housing comprising a plurality of gears and forming support auxiliary machines while ensuring their training.
- a housing comprising a plurality of gears and forming support auxiliary machines while ensuring their training.
- the radial shaft or drive shaft passes through the two primary flow and secondary flow veins respectively because the accessory gearbox, also called AGB for "Accessory Gear Box” ", Is mounted on the housing of the fan generating the secondary flow.
- a known drive shaft is formed of two elements called primary shaft and secondary shaft.
- the first shaft element or primary shaft is connected at one of its ends to a mechanical transmission means with a turbojet engine shaft.
- the second shaft element or secondary shaft is connected at one of its ends to a mechanical transmission means with the accessory gearbox.
- An intermediate support bearing of the drive shaft can be arranged in a section of the radial arm.
- Such an intermediate bearing generally comprises a plurality of bearings for supporting the drive shaft when it is rotating.
- the radial arm of the intermediate casing is subjected to aerodynamic forces.
- the deformations induced by these aerodynamic forces on the radial arm cause the appearance of a first misalignment of the drive shaft at the connection of the first shaft element and the second shaft element and a second misalignment of the drive shaft at the intermediate bearing.
- These misalignments thus appear in different areas and produce unbalance and vibrations of the drive shaft in the radial arm, including inducing a moment in the bearings of the intermediate bearing, which reduces the drive efficiency of the drive. 'tree.
- the present invention aims to overcome these disadvantages. It relates to a turbojet, in particular a multi-flow turbojet, comprising an intermediate casing with radial arms and a gearbox drive shaft of auxiliary machines of the turbojet engine mounted in a radial arm of the intermediate casing.
- the radial arm of the intermediate casing comprises an intermediate support bearing of the drive shaft.
- the intermediate bearing comprises a plurality of support bearings of the drive shaft.
- the drive shaft comprises a first shaft element, connected at one end to a mechanical transmission means with a turbojet engine shaft, and a second shaft element connected at one end to a mechanical transmission means with gearbox of auxiliary machinery.
- the first shaft element and the second shaft element are connected by a connection consisting of a fitting of one end of the second shaft element into a hollow cylindrical end of the first shaft element and being carried out by a plurality of complementary splines disposed on the first shaft member and the second shaft member.
- the turbojet is remarkable in that a same plane transversely cuts the plurality of grooves and the plurality of bearings.
- the first shaft element and the second drive shaft element are articulated around a spigot center and the same plane transversely crosses said spigot center and the plurality of bearings.
- This further facilitates swiveling of the first shaft member and the second shaft member due to deflection in the radial arm of the intermediate housing.
- This makes it possible to reduce the unbalance and the vibrations of the drive shaft since the swiveling center of the drive shaft, located at the level of the connection between the first shaft element and the second element of the drive shaft.
- shaft, and more particularly at the splines of the link is brought to the level of the intermediate bearing, that is to say in a swiveling plane of the drive shaft.
- the same plane transversely cuts the center of swiveling and the center of each bearing of the plurality of bearings.
- This further facilitates swiveling of the first shaft member and the second shaft member due to deflection in the radial arm of the intermediate housing.
- This further reduces the unbalance and vibration of the tree for driving, since the swivel center of the drive shaft, situated at the level of the connection between the first shaft element and the second shaft element, and more particularly at the level of the splines of the link, is brought back to a median plane passing through the centers of the intermediate bearing bearings, that is to say the median plane of support of the drive shaft by the bearings of the intermediate bearing.
- the same plane transversely cuts the middle of each groove of the plurality of grooves and the middle of each bearing of the plurality of bearings.
- This makes it possible to place the center of swiveling of the link, when it is in a transverse plane comprising the middle of each groove, in the median plane of support of the drive shaft.
- the swiveling movement of the link thus has its origin in the median plane of support of the drive shaft, which further reduces the unbalance and vibrations of the drive shaft while increasing the amplitude of the drive.
- swiveling of the first shaft member relative to the second shaft member as the swivel center of the first shaft member relative to the second shaft member is at the splines.
- Flexible swiveling of the drive shaft can further be achieved by using curved splines, thereby increasing the swiveling amplitude of the first shaft element relative to the second shaft element, while decreasing with the configuration. according to the invention, the unbalance and vibrations.
- the first drive shaft element is housed in a first sleeve and the second drive shaft element is housed in a second sleeve.
- the intermediate bearing is housed in a space of the radial arm forming separation of the primary flow from the secondary flow.
- a lubricating oil injection device arranged for injecting lubricating oil at a plane traversing transversely the plurality of grooves and the plurality of bearings.
- the turbojet engine further comprises an outer race of the intermediate bearing bearing centered in the housing. This improves the positioning of the shaft line by minimizing the stacking of tolerances. This also closes the oil chamber formed by the housing and participates in its sealing by compressing the seal installed in the groove of the housing. This also allows the centering and sealing of the secondary sheath.
- FIG. 1 shows, in axial section, a general view of a double-body, dual-flow turbojet engine on which the invention is applicable
- FIG. 2 shows a rear view of a turbojet engine comprising an intermediate crankcase. right of it;
- Figure 3 schematically shows a radial arm of the intermediate casing in which is housed a drive shaft
- FIG. 4 illustrates a sectional view of a radial arm of the intermediate casing in which is housed a drive shaft of a turbojet according to the invention; illustrates a sectional view of an intermediate bearing of a radial arm of the intermediate casing in which is housed a drive shaft of a turbojet according to the invention;
- Figure 6 schematically illustrates a sectional view of an intermediate bearing of a radial arm of the intermediate casing in which is housed a drive shaft.
- a turbojet engine 10 with double flow and double body with its various main components is illustrated schematically in FIG. It comprises a first shaft 3 connecting, on the left in the figure, a fan rotor 5 and the first compressor stages 7 to the low-pressure turbine 9; the whole forms the low pressure body, BP.
- a second drum-shaped shaft 11 connects the high pressure stages 13 of the compressor to the high pressure turbine 15; the assembly forms the HP high pressure body with the combustion chamber (not shown).
- the shaft 3 is supported, upstream, by the bearings 3a and 3a 'mounted on the casing 30 which is designated intermediate casing and, downstream, by the bearing 3c mounted on the exhaust casing 21.
- the shaft HP is supported here by the bearing 3b of the intermediate casing 30 and at the rear of the shaft 3 via the inter-shaft bearing 3d.
- the intermediate casing 30 is composed of a hub 30a supporting the bearings 3a, 3a 'and 3b, of an outer ring 30b, provided with means for attaching the aircraft to the aircraft and supporting the fan casing, as well as radial arms 30c, illustrated in Figure 2, connecting the hub 30a to the ferrule 30b.
- This intermediate casing 30 is constituted at least in part by a foundry piece on which there may have been radial arms.
- Auxiliary machines, such as generators and fuel or oil pumps, are mounted on a gearbox 20, as is known, referred to in the art as AGB.
- This housing is mounted externally on the fan housing at a location that allows access for maintenance.
- the gears are mechanically connected to a motor shaft via a radial drive shaft 100, shown schematically in FIG. 3, which is housed in a radial arm 30c of the intermediate casing 30.
- the arm 30c is hollow and is formed of three radially distinct portions, as shown in FIG. 4: 30c1, 30c2 and 30c3.
- the aerodynamically profiled portion 30c3 passes through the vein of the primary flow P between the LP compressor and the HP compressor (not shown).
- the portion 30c3 of the arm 30c is adjacent to the hub 30a of the intermediate casing 30.
- the radial arm 30c comprises a portion 30c2 through the secondary flow stream S.
- the portion 30c2 is adjacent to the ferrule 30b.
- the arm 30c comprises a portion 30c1 between the first two. This part delimits an annular space sector which extends on one side the separation nozzle between the primary and secondary flows, and on the other side extends itself by an annular space 129 between the two flows.
- such a motor sucks the air through the blower which compresses it into a primary flow which passes through the compression stages, the combustion chamber and the turbine stages and a secondary flow which is ejected into the atmosphere by bypassing the combustion chamber.
- the turbines drive the compression means via BP and HP trees respectively.
- an intermediate bearing 1 10 makes it possible to support the drive shaft 100 between the ends respectively connected to the mechanical transmission means with the drive shaft 3 of the turbojet engine 10 and by means of mechanical transmission with the gearbox 20 drive accessories.
- the bearing 1 10 comprises a housing 1 10a, a housing 1 10b and a plurality of bearings 1 15. These bearings 1 15 both support the drive shaft 100 and promote rotation. These bearings may be of the barrel roll type known to those skilled in the art.
- the drive shaft 100 comprises a first shaft element or primary shaft 101.
- the first shaft element 101 is placed in a primary sleeve 51, connected to the casing 1 10a of the intermediate bearing 1 10 and housed in the radial arm 30c of the intermediate casing 30.
- This first shaft element 101 is connected to a first pinion conical at its inner radial end.
- This pinion is engaged with a conical pinion integral with the HP body.
- the driving shaft 100 also comprises, as illustrated in FIGS. 3 to 6, a second shaft element or secondary shaft 102.
- the second shaft element 102 is placed in a secondary sheath 52, connected at one end to the ferrule 30b and the other end to the casing 1 10b of the intermediate bearing 1 10, and housed in the radial arm 30c of the intermediate casing 30.
- This second shaft element 102 is connected to a second pinion at its outer radial end which is engaged with an input shaft of the gearbox 20.
- Suitable seals seal between the intermediate casing 30 and the two sleeves 51 and 52. Similarly, seals are provided at the other two ends of the two sleeves 51 and 52.
- the shaft 100 passes through the collar 30b of the intermediate casing and its outer radial end is mechanically connected, for example by a splined connection, to a pair of bevel gears 126 shown in FIG. 4.
- the linkage 105 consists of a fitting of one end of the second shaft member 102 in a hollow cylindrical end of the first shaft member 101 and is formed by complementary splines 107 disposed on the first shaft member 101 and the second shaft member 102.
- This plurality of splines Complementary mounts thus allow nesting of the second shaft element 102 in the first shaft element 101 while making the first shaft element 101 and the second shaft element 102 integral in rotation.
- the first shaft member 101 is connected by a splined connection to a pair of bevel gears 126 engaged with a pin of the HP body (not shown).
- the radial end of the second shaft element 102 is mechanically connected by a pair of bevel gears (not shown) to the input shaft of the gearbox 20.
- the rotational movement of the HP body is thus transmitted by the means transmission device constituted by the pair of bevel gears 126 and the drive shaft 100 to the input shaft of the gearbox 20.
- the same plane transversely cuts the plurality of grooves 107 and the plurality of bearings 1 15.
- the articulation of the link 105 is made at the level of the support zone formed by the plurality of bearings 1 15.
- the articulation of the link 105, generated by the aerodynamic forces undergone by the turbojet engine 10 in operation, is produced, as illustrated in FIG. 6, around a center of spindle 210.
- FIGS. 4 to 6 illustrates the case where the same plane transversely cuts the swivel center 210 and the plurality of bearings 1 15, thus making it possible to center the swiveling of the connection 105 at the level of the plurality of bearings. 1 15 and thus reduce the play of the drive shaft 100 in the radial arm 30c.
- the same plane 200 crosses transversely the swiveling center 210 and the center of each bearing of the plurality of bearings 1 15. This allows articulating the swiveling of the link 105 in the median plane transverse to the bearings 1 15, further reducing the clearances caused for example by the turbojet engine 10 in operation.
- the same plane transversely cuts the center of each groove of the plurality of grooves 107 the center of each bearing of the plurality of bearings 1 15. This corresponds to the particular case where the swiveling center is in the plane transverse beam passing through the center of each groove of the plurality of flutes 107.
- the grooves 107 may be curved to improve the swiveling of the connection 105.
- the intermediate bearing 1 10 may thus comprise a housing 120 for supplying the oil necessary for the lubrication of the drive shaft 100 and the mechanical transmission elements by a circuit which does not interfere with the radial arms 30c of the intermediate casing 30.
- the oil is supplied by a dedicated device 122 installed in the housing 120, in order to directly inject the oil at the intermediate bearing 1 10 to perform the lubrication.
- the oil can be brought directly to the grooves 107 and the bearings 1 15, improving the efficiency of the bearings 1 15 and therefore the support, through the link 105, of the drive shaft 100.
- the outer race 125 of the intermediate bearing bearing 1 10 is centered directly in the housing 120, thus improving the positioning of the shaft line by minimizing the stacking of the tolerances. It is fixed to the housing 120 by a plurality of bolts 130. Its particular shape makes it possible to close the oil enclosure formed by the housing 120, and participates in its sealing by compressing the seal 135 installed in the groove of the housing 120. centering and sealing the secondary sheath 52. Meanwhile, the housing 120 ensures the centering and sealing of the primary sheath 51.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Transportation (AREA)
- Rolling Contact Bearings (AREA)
- Mounting Of Bearings Or Others (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- General Details Of Gearings (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BR112013021050-8A BR112013021050B1 (pt) | 2011-02-21 | 2012-02-17 | motor turbojato multi-fluxo que compreende uma carcaça intermediária com braços radiais e um eixo de acionamento |
JP2013553989A JP6010555B2 (ja) | 2011-02-21 | 2012-02-17 | ターボジェットエンジンの補機のギアボックス用ドライブシャフト |
CA2827014A CA2827014C (fr) | 2011-02-21 | 2012-02-17 | Arbre d'entrainement de boitier a engrenages de machines auxiliaires d'un turboreacteur |
RU2013138448/06A RU2582375C2 (ru) | 2011-02-21 | 2012-02-17 | Приводной вал коробки зубчатых передач вспомогательных механизмов турбореактивного двигателя |
EP12709936.4A EP2678543B8 (fr) | 2011-02-21 | 2012-02-17 | Arbre d'entrainement de boitier a engrenages de machines auxiliaires d'un turboreacteur |
CN201280009449.3A CN103380279B (zh) | 2011-02-21 | 2012-02-17 | 用于涡轮喷气发动机引擎的辅助机器的齿轮箱的驱动轴 |
US14/000,314 US9796264B2 (en) | 2011-02-21 | 2012-02-17 | Driveshaft for the gearbox of auxiliary machines of a turbojet engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1151381A FR2971816B1 (fr) | 2011-02-21 | 2011-02-21 | Arbre d'entrainement de boitier a engrenages de machines auxiliaires d'un turboreacteur |
FR1151381 | 2011-02-21 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012114029A1 true WO2012114029A1 (fr) | 2012-08-30 |
Family
ID=45873171
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/050354 WO2012114029A1 (fr) | 2011-02-21 | 2012-02-17 | Arbre d'entrainement de boitier a engrenages de machines auxiliaires d'un turboreacteur |
Country Status (9)
Country | Link |
---|---|
US (1) | US9796264B2 (fr) |
EP (1) | EP2678543B8 (fr) |
JP (1) | JP6010555B2 (fr) |
CN (1) | CN103380279B (fr) |
BR (1) | BR112013021050B1 (fr) |
CA (1) | CA2827014C (fr) |
FR (1) | FR2971816B1 (fr) |
RU (1) | RU2582375C2 (fr) |
WO (1) | WO2012114029A1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2016531226A (ja) * | 2013-06-21 | 2016-10-06 | スネクマ | ターボ機械用の改良型中間ケーシングおよび補機ギアボックス駆動アセンブリ |
US20170122122A1 (en) * | 2014-06-12 | 2017-05-04 | Safran Aircraft Engines | A turbine engine comprising a drive system for a device such as an accessories case |
WO2017187091A1 (fr) * | 2016-04-28 | 2017-11-02 | Safran Aircraft Engines | Bras pour carter de turbomachine comprenant une pièce additionnelle amovible |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011112250A1 (de) * | 2011-09-02 | 2013-03-07 | Rolls-Royce Deutschland Ltd & Co Kg | Hilfsgerätegetriebeeinrichtung für ein Triebwerk |
FR3021358B1 (fr) * | 2014-05-23 | 2018-07-20 | Safran Aircraft Engines | Boite d'engrenages de turbomachine d'aeronef |
FR3023585B1 (fr) | 2014-07-09 | 2016-07-15 | Snecma | Carter intermediaire pour un turboreacteur |
RU2605161C1 (ru) * | 2015-10-29 | 2016-12-20 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Валопровод газотурбинного двигателя и способ его сборки |
KR101881057B1 (ko) * | 2015-11-04 | 2018-07-23 | (주)에이스텍 | 클린룸 천정용 모듈식 조립패널 |
FR3071868B1 (fr) * | 2017-10-02 | 2019-09-27 | Safran Aircraft Engines | Bras pour carter de turbomachine comprenant un corps et une piece amovible |
US11131247B2 (en) | 2018-01-30 | 2021-09-28 | General Electric Company | Additively manufactured rotating shaft |
FR3087424B1 (fr) * | 2018-10-22 | 2021-01-22 | Safran Trans Systems | Systeme de couplage/decouplage de boitiers d'accessoires |
FR3095244B1 (fr) * | 2019-04-17 | 2022-06-24 | Safran Aircraft Engines | Procédé d’utilisation d’une entrée d’air de nacelle de turboréacteur lors d’une phase de poussée et lors d’une phase d’inversion de poussée |
US11603890B2 (en) | 2019-09-18 | 2023-03-14 | Ge Avio S.R.L. | Driveline engagement system |
BE1030550B1 (fr) * | 2022-05-23 | 2023-12-18 | Safran Aero Boosters | Accouplement par profils polygonaux de pompes dans un groupe de lubrification |
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-
2011
- 2011-02-21 FR FR1151381A patent/FR2971816B1/fr not_active Expired - Fee Related
-
2012
- 2012-02-17 CA CA2827014A patent/CA2827014C/fr active Active
- 2012-02-17 EP EP12709936.4A patent/EP2678543B8/fr active Active
- 2012-02-17 US US14/000,314 patent/US9796264B2/en active Active
- 2012-02-17 CN CN201280009449.3A patent/CN103380279B/zh active Active
- 2012-02-17 BR BR112013021050-8A patent/BR112013021050B1/pt active IP Right Grant
- 2012-02-17 RU RU2013138448/06A patent/RU2582375C2/ru active
- 2012-02-17 JP JP2013553989A patent/JP6010555B2/ja active Active
- 2012-02-17 WO PCT/FR2012/050354 patent/WO2012114029A1/fr active Application Filing
Patent Citations (5)
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JP2001317374A (ja) * | 2000-04-28 | 2001-11-16 | Honda Motor Co Ltd | ガスタービンエンジンの補機駆動ユニット |
JP2003269191A (ja) * | 2002-03-18 | 2003-09-25 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンエンジン |
EP1908941A2 (fr) * | 2006-09-27 | 2008-04-09 | General Electric Company | Assemblage de moteur de turbine à gaz et procédé d'assemblage de celui-ci |
EP1939429A2 (fr) * | 2006-12-21 | 2008-07-02 | General Electric Company | Système de prise de force et ensemble de moteur de turbine à gaz l'incluant |
EP2101052A1 (fr) * | 2008-03-14 | 2009-09-16 | Hispano-Suiza | Assemblage d'engrenages pour l'entraînement d'accessoires d'une turbine à gaz |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2016531226A (ja) * | 2013-06-21 | 2016-10-06 | スネクマ | ターボ機械用の改良型中間ケーシングおよび補機ギアボックス駆動アセンブリ |
US20170122122A1 (en) * | 2014-06-12 | 2017-05-04 | Safran Aircraft Engines | A turbine engine comprising a drive system for a device such as an accessories case |
US9982556B2 (en) * | 2014-06-12 | 2018-05-29 | Safran Aircraft Engines | Turbine engine comprising a drive system for a device such as an accessories case |
RU2681391C2 (ru) * | 2014-06-12 | 2019-03-06 | Сафран Эйркрафт Энджинз | Турбинный двигатель, содержащий систему приводов для такого устройства, как коробка агрегатов |
WO2017187091A1 (fr) * | 2016-04-28 | 2017-11-02 | Safran Aircraft Engines | Bras pour carter de turbomachine comprenant une pièce additionnelle amovible |
FR3050776A1 (fr) * | 2016-04-28 | 2017-11-03 | Snecma | Bras pour carter de turbomachine comprenant une piece additionnelle amovible |
US10760501B2 (en) | 2016-04-28 | 2020-09-01 | Safran Aircraft Engines | Arm for turbine-engine casing comprising a removable additional piece |
Also Published As
Publication number | Publication date |
---|---|
EP2678543B1 (fr) | 2015-04-08 |
RU2582375C2 (ru) | 2016-04-27 |
US20130319140A1 (en) | 2013-12-05 |
CN103380279A (zh) | 2013-10-30 |
FR2971816B1 (fr) | 2015-11-13 |
EP2678543B8 (fr) | 2015-07-01 |
JP2014506973A (ja) | 2014-03-20 |
RU2013138448A (ru) | 2015-03-27 |
BR112013021050A2 (pt) | 2016-10-18 |
EP2678543A1 (fr) | 2014-01-01 |
FR2971816A1 (fr) | 2012-08-24 |
US9796264B2 (en) | 2017-10-24 |
CA2827014C (fr) | 2018-05-22 |
BR112013021050B1 (pt) | 2021-01-26 |
CA2827014A1 (fr) | 2012-08-30 |
CN103380279B (zh) | 2016-01-06 |
JP6010555B2 (ja) | 2016-10-19 |
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