EP1553263A1 - Entretoise pourvue de raccordements des canalisations de service d'un turboréacteur - Google Patents
Entretoise pourvue de raccordements des canalisations de service d'un turboréacteur Download PDFInfo
- Publication number
- EP1553263A1 EP1553263A1 EP05300017A EP05300017A EP1553263A1 EP 1553263 A1 EP1553263 A1 EP 1553263A1 EP 05300017 A EP05300017 A EP 05300017A EP 05300017 A EP05300017 A EP 05300017A EP 1553263 A1 EP1553263 A1 EP 1553263A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- casing
- arm
- modular
- plate
- servitudes
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000012530 fluid Substances 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 4
- 239000000725 suspension Substances 0.000 description 7
- 238000002485 combustion reaction Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000013067 intermediate product Substances 0.000 description 1
- 210000000056 organ Anatomy 0.000 description 1
- 229910052697 platinum Inorganic materials 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
Definitions
- the invention relates to a turbofan engine comprising a outer casing of secondary flow.
- a turbojet engine comprises, functionally, a inlet handle, a blower, a compressor, a chamber of combustion, a turbine and an exhaust nozzle. These various elements are contained in housings.
- an intermediate housing placed just downstream of the retention housing of the blades of blower, and an exhaust casing at the rear of the engine.
- annular secondary airflow is guided on its inner surface by an inner casing called “inner fan duct”, placed globally concentric to outer structural casing, between the inner base of the arms of the intermediate casing and the exhaust casing.
- inner fan duct placed globally concentric to outer structural casing, between the inner base of the arms of the intermediate casing and the exhaust casing.
- the various fluids necessary for the operation of the turbojet such as the fuel, oil and accessory organ control fluids of the motor, must be routed from outside the turbojet engine, in particular outside the structural outer casing, towards its core, that is to say the enclosure, defined by the internal casing, containing the compressor, the chamber of combustion, the turbine and the nozzle.
- This routing is carried out by pipelines commonly referred to as easements.
- the invention relates to particularly the passage of the servitudes between the outer casing of the flow secondary and internal housing.
- FIG 1 which partially represents the elements of the envelope, a turbojet 1 of the prior art, we see an intermediate casing 2 and a 3.
- the ring is attached to the exhaust housing, no represented by connecting rods.
- An external structural casing 4 mounted between the casing 2 and the ring 3 comprises access hatches 5 distributed over its circumference, allowing access to the interior of the enclosure that it defines, and in particular to the housing internal. It is through these hatches 5 that the easements 7 are mounted.
- the internal casing comprises a plurality of panel support plates 6, extending longitudinally between the base of the intermediate casing arm and exhaust housing. They are intended for support panels that will define the surface of the inner housing. Easements 7 are brought and fixed on these panel support plates 6, to which the operator has access through the access hatches 5 of the external structural casing 4, on a sole 8 protruding radially on the plates 6. On this sole 8 is then mounted, between the outer structural casing 4 and non-structural internal casing, a profiled envelopment sleeve of easements 7, to ensure their protection and a good flow of the gas vein. The fitting of the profiled shirt is also by hatches 5. These can then be closed.
- the present invention aims to simplify the assembly, disassembly and maintenance of the servitudes passing between the structural outer casing and the casing internal non-structural of a turbojet.
- a turbofan engine comprising an external secondary flow casing, an internal secondary flow casing, fluid transport servitudes located outside the external flow casing secondary, fluid transport servitudes located inside the housing internal secondary flow, is characterized by the fact that at least one arm removable modular forming servitude connector is arranged between said housing external and said inner housing.
- the connection of external servitudes to the housing secondary flow, at internal servitudes to the internal casing, is made simply using a removable modular arm, it is easy to mount and dismount.
- the arm forms a any compound of a prefefined set of standard elements; his character Removable means the possibility of removing it, as a whole modular.
- This arm can also be calibrated for various applications or different turbojets.
- the non-structural inner housing having panels and longitudinal panels for supporting the panels, at least one plate longitudinal panel support comprises a receiving plate of a removable modular arm.
- the outer casing comprises less a passage opening of a removable modular arm.
- the modular arm comprises pipe elements, comprising external connecting means to easements, and intended to be inserted in channels opening on the face external board.
- the channels also open at least one different face of the plate and comprise connecting means to easements.
- the outer face of the plate comprises a recess receiving the modular arm, in which the channels are drilled.
- the invention concerns, as an intermediate product, a modular arm removable for the turbojet engine shown above, comprising a sheet metal, pierced orifices for the passage of calibrated pipe elements, elements of calibrated pipelines and a profiled jacket adapted to the sheet.
- the pipe elements comprise, at one of their ends, connecting means to servitudes.
- the pipe elements comprise, at one of their ends, an O-ring seal.
- the sheet comprises a recess, on which are drilled the orifices, intended to be fitted into the profiled jacket.
- the turbojet engine 10 of the invention comprises from upstream to downstream in the direction of gas flow, an air intake sleeve, a fan 11, a compressor 12, a combustion chamber 13, a turbine 14 and an exhaust duct 15.
- the blower is contained in a fan retention housing 16, downstream of which is mounted a housing intermediate 17, supported by arms 18 resting on an annular internal base 19 extending around the compressor housing 20.
- the conduit 15 is contained in an exhaust housing 21.
- a suspension ring 22, intended to be attached to a turbojet engine suspension to an airplane, is attached to the crankcase exhaust 21 by not shown rods.
- an internal casing 23 non-structural commonly called “inner fan duct”, which envelops the heart of the turbojet engine 10, for the purpose to contain and guide the secondary flow flowing outside of the latter.
- an outer casing secondary flow 24 structural, commonly called “outer fan duct”, whose role is to contain and guide, on its external surface, the secondary flow flowing outside the heart of the turbojet engine 10, but also to take up the thrust forces between the ring of suspension 22 and the intermediate casing 17, to which is connected the other suspension from the turbojet engine 10 to the airplane.
- a modular radial arm 25 servitudes is arranged, for the purpose of connecting servitudes, between the crankcase 24 and the inner casing 23. Its role is to ensure continuity between servitudes located outside the external flow casing 24 and other located inside the inner housing 23.
- the modular arm 25 comprises a plate 26 overall rectangular, slightly curved, in which is practiced a recess 27, here of oval shape.
- a recess 27 In the recess 27 are drilled orifices 28 for passage of pipe elements 29, here ten in number. More precisely, in each orifice 28, a pipe element 29 can be inserted and fixed, for example by bolting, at this orifice 28, as it will be seen more precisely further.
- the pipe elements 29 are here metallic.
- Each pipe element 29 is a service coupling, between a servitude outside the outer casing 24 and its extension inside the internal casing 23.
- Each duct element 29 is calibrated according to the servitude for which it provides the function of connection.
- the diameter of the orifice 28 is calibrated according to the pipe element 29 that it receives.
- each line element 29 comprises a skirt 31 for positioning and sealing, which is integral with it and is intended to abut on the inner face of the recess 27.
- each pipe element 29 is inserted, by its end closest to the skirt 31, in the orifice 28 which is intended for it, until the skirt 31 abuts the inner face of the recess 27.
- a nut 30 is then screwed onto a thread of the pipe element 29 provided for this purpose, the outer side of the recess 27, ensuring the maintenance of the pipe element 29 in its orifice 28, between the nut 30 and the skirt 31.
- Other intermediate sealing or positioning parts, in particular outer side of the recess 27, may be provided.
- connection means 50 connect the service on the outside of the outer casing 24, and for which it is desired to provide a connection with an easement within the enclosure defined by the inner casing 23, to the pipe element 29, which has been previously sized to ensure this connection.
- All the pipe elements 29 are fixed in their orifice 28 respective.
- the same number of orifices 28 are provided as elements of 29. If this were not the case, the unused ports 28 would be blocked.
- the elements of pipes 29 have an elbow 32 near their skirt 31 and extend in a generally rectilinear manner on either side of this elbow 32.
- pipe elements 29 all have the same shape, except for their diameter, and therefore extend all parallel to each other once mounted.
- the removable modular arm 25 of the invention further comprises a profiled shirt 33.
- the shirt 33 has a body of shirt 34 of generally oval section, corresponding to the oval shape of the recess 27, and elongated so as to adapt to the distance separating the housing internal 23 of the outer casing 24.
- the jacket 33 is hollow and open from both sides, and has an outer rim 35, generally perpendicular to the body 34, and whose shape corresponding to the shape of the sheet 26.
- the oval shape is linked initially to the oval shape that we wish give the liner 33 of the modular arm 35. Indeed, once the turbojet mounted, the jacket 33 extends between the inner casing 23 and the outer casing 24, by consequently, in the secondary stream, its shape must be adapted according to the flow of the secondary flow around it.
- the oval shape can of course be replaced by any appropriate form.
- the modular arm 25 of the invention once assembled, comprises the plate 26, on which are fixed the pipe elements 29, around which is threaded the profiled jacket 33, whose shape adapts to the whole.
- the rim 35 of the jacket 33 is arranged, as we saw earlier, to fit the shape of the inner face of the sheet 26, the recess 27 of the sheet being embedded, on the inner side where it protrudes, in the body 34 of the sleeve 33, dimensioned for this purpose.
- the liner 33 is made integral, by welding or brazing, for example, sheet metal 26, forming, with it and the pipe elements 29, the modular arm 25 of the invention.
- the inner casing 23 comprises a plurality of longitudinal plates panel supports 36, here four in number, which form, with other holding elements such as a ring 37, the armature of the internal casing 23.
- the inner casing 23 is formed when panels 38 are placed between the successive panel supports 36, wedged in recesses 47 provided for this purpose, thereby creating the surface required for the enveloping of the heart of the turbojet engine 10 and the flow guidance secondary.
- a plate 39 for receiving an arm modular connection 25 servitudes.
- a plate 39 includes a longitudinal recess 40, forming a shoulder 41 which follows a shape globally oval corresponding to the section of the inner end of the sleeve 33 of the modular arm 25.
- the recess 40 is pierced with a plurality of channels 42, here at the number of ten, receiving and connecting elements of conduits 29 of the modular arm 25 of the invention.
- Each channel 42 includes a portion 43 opening on the surface of the recess 40, here in front view perpendicular to this surface, an elbow 51 and a portion 44 parallel to the surface of the recess 40, therefore perpendicular to the first portion 43, opening onto a lateral longitudinal wall of the support 36 in which the channel 42 is pierced.
- two parallel rows of five channels 42 are drilled on the recess 40, the channels 42 opening, depending on the row to which they belong to one or other of the lateral longitudinal walls of the support 36. It goes without saying that instead of opening onto the lateral faces of the support 36, the Channels 42 could lead to its inner face.
- a servitude 45 located inside the enclosure defined by the internal casing 23.
- Fittings 46 well known to those skilled in the art, may be provided for this purpose on the support 36.
- the connectors 46 and the channels 42 are well sure sized according to the servitude to which they must serve as connection.
- Each channel 42 is dimensioned, in its portion 43 opening on the surface of the recess 40, for receiving the end of a pipe element 29.
- the latter may be provided with an O-ring 48 sealing.
- the ten channels 42 are dimensioned to receive each end of the pipe element 29 of the modular arm 25 corresponding to their position.
- the distribution and the diameter of the channels 42 on the surface of the recess 40 of the support 36 is comparable to the distribution and the diameter of the orifices 28. on the surface of the recess 27 of the modular arm 25.
- the plate 39 is exactly arranged and designed for the reception of a modular arm 25 particular: its channels 42 are arranged to receive the elements of 29, while the shoulder 41 of the recess 40 is arranged to support the inner end of the body 34 of the shirt 33.
- the panel supports 36 of the internal casing 23 of the turbojet engine 10 are mounted around the heart of the turbojet engine 10, between the internal base 19 of the arm 18 of the intermediate casing 17 and the exhaust casing 21.
- the easements, extending inside the enclosure which will be defined by the inner housing 23 and intended to be connected with servitudes located outside the housing external 24, are then connected to the portions 43 of the channels 42 which are intended, on the connections 46, provided for this purpose, the support 36 on which is arranged the plate 39 for receiving the modular arm 25.
- the modular arm 25 is then slid through a hole 49 oval provided for this purpose on the outer casing 24, between the latter and the inner casing 23.
- the orifice 49 is at the base of the plate 39, so that it is possible, just by inserting the arm 25 into the orifice 49, to insert the ends of the elements of pipes 29 in the portions 43 of pipes 42 of the platinum 39 intended to receive them, without the need to access the space defined by the inner casing 23 and the outer casing 24.
- the plate 26 of the arm 25 is then fixed removably to the outer structural casing 24, for example by means of inserts, or any other suitable means. It could also be brazed, this which would, however, make it more difficult to disassemble the arm 25.
- the connection of the servitudes between the outer structural casing 24 and the non-structural internal casing 23 is assured, the arm 25, in cooperation with the plate 39 and the orifice 49 of the outer structural casing 24, allowing the connection of servitudes here.
- This connection can be easily removed and dismounted without having to disassemble internal connection made at the side walls of the supports 36.
- the modular arm 25, its orifices 28 for passage of pipe elements 29, the pipe elements 29 and their connections 50, the channels 42 and their connectors 46 are calibrated according to the servitudes they allow to connected. It goes without saying that all of these elements could be calibrated standard way, fittings 46, 50 or other fittings allowing adaptation according to the type and size of easements to be connected.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- la figure 1 représente une vue schématique en perspective d'une enveloppe de turboréacteur de l'art antérieur ;
- la figure 2 représente une vue schématique en perspective des servitudes montées sur une plaque de support de carter interne de l'art antérieur ;
- la figure 3 représente une vue de profil en coupe du turboréacteur de l'invention ;
- la figure 4 représente une vue schématique en perspective d'une partie du bras modulaire de l'invention ;
- la figure 5 représente une vue de dessous schématique en perspective partiellement en coupe du bras modulaire de l'invention ;
- la figure 6 représente une vue schématique en perspective d'une autre partie du bras modulaire de l'invention ;
- la figure 7 représente une vue de profil du bras modulaire de l'invention ;
- la figure 8 représente une vue schématique en perspective des supports de panneaux du carter interne non structural du turboréacteur de l'invention ;
- la figure 9 représente une vue en coupe transversale d'un support de panneaux du carter interne non structural du turboréacteur, dans lequel sont insérés des éléments de canalisations du bras modulaire de l'invention, et
- la figure 10 représente une vue schématique de face en perspective du turboréacteur de l'invention.
Claims (10)
- Turboréacteur à double flux, comprenant un carter externe de flux secondaire (24), un carter interne de flux secondaire (23), des servitudes de transport de fluide situées à l'extérieur du carter externe de flux secondaire (24), des servitudes de transport de fluide situées à l'intérieur du carter interne de flux secondaire (23), caractérisé par le fait qu'au moins un bras modulaire amovible (25) formant raccord de servitudes est agencé entre ledit carter externe (24) et ledit carter interne (23).
- Turboréacteur selon la revendication 1, dans lequel, le carter interne (23) comprenant des panneaux (38) et des plaques longitudinales de support des panneaux (36), au moins une plaque longitudinale de support de panneaux (36) comprend une platine (39) de réception d'un bras modulaire amovible (25).
- Turboréacteur selon l'une des revendications 1 ou 2, dans lequel le carter externe (24) comprend au moins un orifice (49) de passage dudit bras modulaire (25).
- Turboréacteur selon l'une des revendications 2 ou 3, dans lequel ledit bras modulaire (25) comprend des éléments de canalisations (29), pourvus de moyens externes (50) de raccord à des servitudes, et destinés à être insérés dans des canaux (42) débouchant sur la face externe de la platine (39).
- Turboréacteur selon la revendication 4, dans lequel les canaux (42) débouchent également sur au moins une face différente de la platine (39) et comprennent des moyens (46) de raccord à des servitudes.
- Turboréacteur selon l'une des revendications 4 ou 5, dans lequel la face externe de la platine (39) comprend un évidement (40) de réception du bras modulaire (25), dans lequel sont percés les canaux.
- Bras modulaire pour le turboréacteur de l'une des revendications 1 à 6, comportant une tôle (26), percée d'orifices (28) de passage d'éléments de canalisations (29), des éléments de canalisations (29) et une chemise profilée (33) s'adaptant à la tôle (26).
- Bras modulaire selon la revendication 7, dans lequel les éléments de canalisations (29) comportent, à l'une de leurs extrémités, des moyens de raccord (50) à des servitudes.
- Bras modulaire selon l'une des revendications 7 ou 8, dans lequel les éléments de canalisations (29) comportent, à l'une de leurs extrémités, un joint torique d'étanchéité (48).
- Bras modulaire selon l'une des revendications 7 à 9, dont ladite tôle (26) comprend un renfoncement (27), sur lequel sont percés lesdits orifices (28), destiné à être emmanché dans la chemise profilée (33).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0400221A FR2865001B1 (fr) | 2004-01-12 | 2004-01-12 | Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes. |
FR0400221 | 2004-01-12 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1553263A1 true EP1553263A1 (fr) | 2005-07-13 |
EP1553263B1 EP1553263B1 (fr) | 2016-05-18 |
Family
ID=34586487
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05300017.0A Active EP1553263B1 (fr) | 2004-01-12 | 2005-01-11 | Entretoise pourvue de raccordements des canalisations de service d'un turboréacteur |
Country Status (8)
Country | Link |
---|---|
US (1) | US7543442B2 (fr) |
EP (1) | EP1553263B1 (fr) |
JP (1) | JP4188323B2 (fr) |
CN (1) | CN1657757B (fr) |
CA (1) | CA2492166C (fr) |
FR (1) | FR2865001B1 (fr) |
RU (1) | RU2388921C2 (fr) |
UA (1) | UA85824C2 (fr) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2905975A1 (fr) * | 2006-09-20 | 2008-03-21 | Snecma Sa | Conduite de soufflante pour une turbomachine. |
FR2996070A1 (fr) * | 2012-09-21 | 2014-03-28 | Snecma | Systeme de guidage de cable dans une veine de turbomachine |
FR3036437A1 (fr) * | 2015-05-22 | 2016-11-25 | Snecma | Ensemble de turbomachine pour lubrifier un support de palier |
FR3097258A1 (fr) * | 2019-06-14 | 2020-12-18 | Safran Aircraft Engines | Systeme de passage de servitudes a encombrement optimise des servitudes et a montage simplifie |
WO2021234279A1 (fr) * | 2020-05-20 | 2021-11-25 | Safran Nacelles | Nacelle pour ensemble propulsif à très grand taux de dilution, comprenant une structure interne avant amovible et structurelle |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20060032974A1 (en) * | 2004-08-16 | 2006-02-16 | Honeywell International Inc. | Modular installation kit for auxiliary power unit |
US7624581B2 (en) * | 2005-12-21 | 2009-12-01 | General Electric Company | Compact booster bleed turbofan |
US20080072566A1 (en) * | 2006-09-27 | 2008-03-27 | Pratt & Whitney Canada Corp. | Bleed holes oriented with gaspath and flared for noise reduction |
FR2919347B1 (fr) * | 2007-07-26 | 2009-11-20 | Snecma | Enveloppe externe de conduite de soufflante dans une turbomachine. |
FR2919344B1 (fr) * | 2007-07-26 | 2013-08-16 | Snecma | Turboreacteur a double flux comprenant une conduite de soufflante a un seul bras de passage de servitudes. |
FR2933070B1 (fr) * | 2008-06-25 | 2010-08-20 | Snecma | Systeme propulsif d'aeronef |
FR2937301B1 (fr) * | 2008-10-22 | 2010-12-10 | Snecma | Avion a groupes motopropulseurs partiellement encastres dans le fuselage |
US9478896B2 (en) | 2011-12-22 | 2016-10-25 | Rolls-Royce Plc | Electrical connectors |
GB2497807B (en) | 2011-12-22 | 2014-09-10 | Rolls Royce Plc | Electrical harness |
GB2498006B (en) | 2011-12-22 | 2014-07-09 | Rolls Royce Plc | Gas turbine engine systems |
GB2497809B (en) * | 2011-12-22 | 2014-03-12 | Rolls Royce Plc | Method of servicing a gas turbine engine |
EP2900956B1 (fr) * | 2012-09-26 | 2019-11-20 | United Technologies Corporation | Moteur à turbine à gaz avec un ensemble d'étanchéité pour une structure statique |
US9376935B2 (en) | 2012-12-18 | 2016-06-28 | Pratt & Whitney Canada Corp. | Gas turbine engine mounting ring |
FR3015569B1 (fr) * | 2013-12-19 | 2019-01-25 | Safran Aircraft Engines | Carter pour un ensemble propulsif |
FR3034465B1 (fr) * | 2015-04-03 | 2017-05-05 | Snecma | Turbomoteur comportant deux flux de ventilation distincts |
US11230995B2 (en) | 2017-11-08 | 2022-01-25 | Raytheon Technologies Corporation | Cable conduit for turbine engine bypass |
US10727656B2 (en) * | 2017-11-08 | 2020-07-28 | Raytheon Technologies Corporation | Igniter cable conduit for gas turbine engine |
GB201820505D0 (en) * | 2018-12-17 | 2019-01-30 | Rolls Royce | Connector system |
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US4987736A (en) * | 1988-12-14 | 1991-01-29 | General Electric Company | Lightweight gas turbine engine frame with free-floating heat shield |
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US5746574A (en) * | 1997-05-27 | 1998-05-05 | General Electric Company | Low profile fluid joint |
US20020076320A1 (en) * | 2000-12-19 | 2002-06-20 | Glover Samuel L. | Machined fan exit guide vane attachment pockets for use in a gas turbine |
US20030019205A1 (en) | 1998-08-11 | 2003-01-30 | Rice Edward Claude | Method and apparatus for spraying fuel within a gas turbine engine |
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US3841089A (en) * | 1973-02-20 | 1974-10-15 | Ltv Aerospace Corp | Fuel reclaiming system |
US5174110A (en) * | 1991-10-17 | 1992-12-29 | United Technologies Corporation | Utility conduit enclosure for turbine engine |
US5313780A (en) * | 1992-12-07 | 1994-05-24 | General Electric Company | Free-riding oil tube damper |
US7370467B2 (en) * | 2003-07-29 | 2008-05-13 | Pratt & Whitney Canada Corp. | Turbofan case and method of making |
-
2004
- 2004-01-12 FR FR0400221A patent/FR2865001B1/fr not_active Expired - Lifetime
-
2005
- 2005-01-10 CA CA2492166A patent/CA2492166C/fr active Active
- 2005-01-10 UA UAA200500229 patent/UA85824C2/uk unknown
- 2005-01-10 US US11/031,004 patent/US7543442B2/en active Active
- 2005-01-11 JP JP2005003400A patent/JP4188323B2/ja active Active
- 2005-01-11 EP EP05300017.0A patent/EP1553263B1/fr active Active
- 2005-01-11 RU RU2005100180/06A patent/RU2388921C2/ru active
- 2005-01-12 CN CN2005100041680A patent/CN1657757B/zh active Active
Patent Citations (5)
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US4987736A (en) * | 1988-12-14 | 1991-01-29 | General Electric Company | Lightweight gas turbine engine frame with free-floating heat shield |
EP0601864A1 (fr) * | 1992-12-10 | 1994-06-15 | General Electric Company | Cadre pour turbine |
US5746574A (en) * | 1997-05-27 | 1998-05-05 | General Electric Company | Low profile fluid joint |
US20030019205A1 (en) | 1998-08-11 | 2003-01-30 | Rice Edward Claude | Method and apparatus for spraying fuel within a gas turbine engine |
US20020076320A1 (en) * | 2000-12-19 | 2002-06-20 | Glover Samuel L. | Machined fan exit guide vane attachment pockets for use in a gas turbine |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2905975A1 (fr) * | 2006-09-20 | 2008-03-21 | Snecma Sa | Conduite de soufflante pour une turbomachine. |
EP1902952A1 (fr) * | 2006-09-20 | 2008-03-26 | Snecma | Conduite de soufflante pour une turbomachine |
US8136362B2 (en) | 2006-09-20 | 2012-03-20 | Snecma | Turbomachine fan duct |
RU2452865C2 (ru) * | 2006-09-20 | 2012-06-10 | Снекма | Канал вентилятора для газотурбинного двигателя |
FR2996070A1 (fr) * | 2012-09-21 | 2014-03-28 | Snecma | Systeme de guidage de cable dans une veine de turbomachine |
FR3036437A1 (fr) * | 2015-05-22 | 2016-11-25 | Snecma | Ensemble de turbomachine pour lubrifier un support de palier |
WO2016189234A1 (fr) * | 2015-05-22 | 2016-12-01 | Safran Aircraft Engines | Ensemble de turbomachine pour lubrifier un support de palier |
US10557376B2 (en) | 2015-05-22 | 2020-02-11 | Safran Aircraft Engines | Turbine engine unit for lubricating a bearing holder |
FR3097258A1 (fr) * | 2019-06-14 | 2020-12-18 | Safran Aircraft Engines | Systeme de passage de servitudes a encombrement optimise des servitudes et a montage simplifie |
WO2021234279A1 (fr) * | 2020-05-20 | 2021-11-25 | Safran Nacelles | Nacelle pour ensemble propulsif à très grand taux de dilution, comprenant une structure interne avant amovible et structurelle |
FR3110547A1 (fr) * | 2020-05-20 | 2021-11-26 | Safran Nacelles | Nacelle pour ensemble propulsif à très grand taux de dilution, comprenant une structure interne avant amovible et structurelle |
US11891185B2 (en) | 2020-05-20 | 2024-02-06 | Safran Nacelles | Nacelle for a propulsion assembly with a very high bypass ratio, comprising a removable and structural front internal structure |
Also Published As
Publication number | Publication date |
---|---|
EP1553263B1 (fr) | 2016-05-18 |
FR2865001A1 (fr) | 2005-07-15 |
JP4188323B2 (ja) | 2008-11-26 |
CA2492166C (fr) | 2012-06-19 |
JP2005201266A (ja) | 2005-07-28 |
US20050247043A1 (en) | 2005-11-10 |
FR2865001B1 (fr) | 2008-05-09 |
UA85824C2 (uk) | 2009-03-10 |
RU2005100180A (ru) | 2006-06-20 |
CN1657757A (zh) | 2005-08-24 |
CN1657757B (zh) | 2011-05-04 |
RU2388921C2 (ru) | 2010-05-10 |
US7543442B2 (en) | 2009-06-09 |
CA2492166A1 (fr) | 2005-07-12 |
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