EP1553263A1 - Strebe zur Kupplung des Dienstrohres eines Strahltriebwerks - Google Patents

Strebe zur Kupplung des Dienstrohres eines Strahltriebwerks Download PDF

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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
servitudes
modular
plate
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
Application number
EP05300017A
Other languages
English (en)
French (fr)
Other versions
EP1553263B1 (de
Inventor
Jacky Derenes
Georges Mazeaud
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1553263A1 publication Critical patent/EP1553263A1/de
Application granted granted Critical
Publication of EP1553263B1 publication Critical patent/EP1553263B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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.

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  • 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)
EP05300017.0A 2004-01-12 2005-01-11 Strebe zur Kupplung des Dienstrohres eines Strahltriebwerks Expired - Lifetime EP1553263B1 (de)

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 (de) 2005-07-13
EP1553263B1 EP1553263B1 (de) 2016-05-18

Family

ID=34586487

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05300017.0A Expired - Lifetime EP1553263B1 (de) 2004-01-12 2005-01-11 Strebe zur Kupplung des Dienstrohres eines Strahltriebwerks

Country Status (8)

Country Link
US (1) US7543442B2 (de)
EP (1) EP1553263B1 (de)
JP (1) JP4188323B2 (de)
CN (1) CN1657757B (de)
CA (1) CA2492166C (de)
FR (1) FR2865001B1 (de)
RU (1) RU2388921C2 (de)
UA (1) UA85824C2 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
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

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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
GB2498006B (en) 2011-12-22 2014-07-09 Rolls Royce Plc Gas turbine engine systems
US9478896B2 (en) 2011-12-22 2016-10-25 Rolls-Royce Plc Electrical connectors
GB2497809B (en) * 2011-12-22 2014-03-12 Rolls Royce Plc Method of servicing a gas turbine engine
GB2497807B (en) 2011-12-22 2014-09-10 Rolls Royce Plc Electrical harness
US10087847B2 (en) 2012-09-26 2018-10-02 United Technologies Corporation Seal assembly for a static structure of a gas turbine engine
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
FR3156488B1 (fr) * 2023-12-12 2025-11-07 Safran Aircraft Engines Systeme de passage de fluides pour une cloison d’une turbomachine et turbomachine comportant un tel systeme

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EP0601864A1 (de) * 1992-12-10 1994-06-15 General Electric Company Turbinenrahmen
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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RU1254798C (ru) * 1983-11-15 1995-06-27 Запорожское машиностроительное конструкторское бюро "Прогресс" Устройство для дренажа топлива из камеры сгорания газотурбинного двигателя
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Publication number Priority date Publication date Assignee Title
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
EP0601864A1 (de) * 1992-12-10 1994-06-15 General Electric Company Turbinenrahmen
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)

* Cited by examiner, † Cited by third party
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 (de) * 2006-09-20 2008-03-26 Snecma Leitung eines Ventilators für eine Strömungsmaschine
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
CN1657757B (zh) 2011-05-04
CA2492166C (fr) 2012-06-19
EP1553263B1 (de) 2016-05-18
CN1657757A (zh) 2005-08-24
JP4188323B2 (ja) 2008-11-26
RU2388921C2 (ru) 2010-05-10
CA2492166A1 (fr) 2005-07-12
FR2865001B1 (fr) 2008-05-09
UA85824C2 (uk) 2009-03-10
JP2005201266A (ja) 2005-07-28
US7543442B2 (en) 2009-06-09
FR2865001A1 (fr) 2005-07-15
RU2005100180A (ru) 2006-06-20
US20050247043A1 (en) 2005-11-10

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