EP1553263B1 - 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 PDF

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Publication number
EP1553263B1
EP1553263B1 EP05300017.0A EP05300017A EP1553263B1 EP 1553263 B1 EP1553263 B1 EP 1553263B1 EP 05300017 A EP05300017 A EP 05300017A EP 1553263 B1 EP1553263 B1 EP 1553263B1
Authority
EP
European Patent Office
Prior art keywords
casing
modular arm
fan duct
arm
modular
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP05300017.0A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1553263A1 (fr
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 Services SA
SNECMA SAS
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Publication date
Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP1553263A1 publication Critical patent/EP1553263A1/fr
Application granted granted Critical
Publication of EP1553263B1 publication Critical patent/EP1553263B1/fr
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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 an outer casing of secondary flow.
  • a turbojet engine comprises, functionally, an air intake shaft, a fan, a compressor, a combustion chamber, a turbine and an exhaust nozzle. These various elements are contained in housings.
  • an intermediate housing placed just downstream of the fan blade retention housing, and an exhaust casing at the rear of the engine.
  • the secondary air flow must be contained and guided along the turbojet engine to the exhaust casing.
  • a structural external secondary flow casing called “outer fan duct”
  • This outer casing structural secondary flow provides a dual function, contention and guiding the secondary air flow, on the one hand, resumption of thrust forces, on the other.
  • annular secondary air stream is guided on its inner surface by an inner casing called “inner fan duct”, placed generally concentric with the outer structural casing, between the inner base of the arms of the intermediate casing and the exhaust casing.
  • inner fan duct placed generally concentric with the 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 engine such as the fuel, the oil and the engine accessory fluid control fluids, must be conveyed from outside the turbojet engine, in particular the outside of the structural outer casing, to its engine. core, that is to say the enclosure, defined by the inner housing, containing the compressor, the combustion chamber, the turbine and the nozzle.
  • This routing is carried out by pipes commonly called servitudes.
  • the invention particularly relates to the passage of servitudes between the outer casing of the secondary flow and the inner casing.
  • FIG. 1 which partially represents the elements of the casing, a turbojet engine 1 of the prior art, we see an intermediate casing 2 and a suspension ring 3.
  • the ring is fixed to the exhaust casing, not shown, 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 inner casing. It is through these hatches 5 that the easements 7 are mounted.
  • the inner housing has a plurality of panel support plates 6, extending longitudinally between the base of the intermediate housing arms and the exhaust housing. They are intended to support panels that will define the surface of the inner casing.
  • the easements 7 are brought and fixed on these panel support plates 6, to which the operator has access through the access doors 5 of the outer structural casing 4, on a sole 8 projecting radially on the plates 6.
  • On this sole 8 is then mounted, between the outer structural casing 4 and non-structural internal housing, a profiled sleeve wrapping Servitudes 7, to ensure their protection and a good flow of the gas stream.
  • the fitting of the profiled jacket is also done by the trap doors 5. These can then be closed again.
  • the present invention aims to simplify the assembly, disassembly and maintenance of the servitudes passing between the outer structural casing and the non-structural internal casing of a turbojet engine.
  • a turbofan engine comprising an external secondary flow casing, an internal secondary flow casing, fluid transport servitudes located outside the external secondary flow casing, and fluid transport servitudes. located inside the inner casing of secondary flow, is characterized in that at least one removable modular arm forming servitude connection is arranged between said outer casing and said inner casing.
  • the connection of external servitudes to the outer casing of secondary flow, the internal servitudes to the inner housing is achieved simply with the aid of a removable modular arm, which is easy to assemble and disassemble. Indeed, because it is modular, the arm forms a whole composed of a prefefined set of standard elements; its removable character means the possibility of removing it, as a whole modular.
  • This arm can also be calibrated for various different applications or turbojets.
  • the non-structural inner housing having panels and longitudinal panels support plates, at least one longitudinal panel support plate comprises a receiving plate of a removable modular arm.
  • the outer casing comprises at least one passage opening of a removable modular arm.
  • the modular arm comprises pipe elements, comprising external means for connection to servitudes, and intended to be inserted in channels opening on the outer face of the plate.
  • the channels also open on at least one different face of the plate and include connection means to servitudes.
  • the outer face of the plate comprises a receiving recess of the modular arm, in which the channels are drilled.
  • the invention relates, as an intermediate product, a removable modular arm for the turbojet engine shown above, comprising a sheet, pierced with passage openings of calibrated pipe elements, calibrated pipe elements and a profiled jacket s adapting 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, upstream to downstream in the direction of the gas flow, an air inlet duct, 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 casing 16, downstream of which is mounted an intermediate casing 17, supported by arms 18 resting on an annular internal base 19 extending around the casing 20.
  • the duct 15 is contained in an exhaust casing 21.
  • a suspension ring 22, intended to be attached to a suspension of the turbojet engine to an aircraft, is fixed to the exhaust casing 21 by not shown rods.
  • an internal non-structural casing 23 commonly called “inner fan duct”, which envelops the core of the turbojet engine 10, in order to contain and guide the secondary flow flowing out of the latter.
  • an outer casing 24 of structural secondary flow commonly called “outer fan duct”, whose role is to contain and guide, on its external surface, the secondary flow flowing outside the turbojet engine core 10, but also to take up the thrust forces between the suspension ring 22 and the intermediate casing 17, to which is connected the other suspension of the turbojet engine 10 to the aircraft.
  • a radial modular connection arm 25 of servitudes is arranged, for the purpose of connecting servitudes, between the outer casing 24 and the inner casing 23. Its role is to ensure continuity between servitudes located at outside the outer casing of secondary flow 24 and others located inside the inner casing 23.
  • the modular arm 25 comprises a generally rectangular plate, slightly curved, in which is formed a recess 27, here of oval shape.
  • a recess 27 In the recess 27 are pierced orifices 28 for passage of pipe elements 29, here at the number of ten. More specifically, in each orifice 28, a pipe element 29 can be inserted and fixed, for example by bolting, at this orifice 28, as will be seen more precisely later.
  • the pipe elements 29 are metallic here.
  • Each pipe element 29 is a service connection, between a servitude outside the outer casing 24 and its extension inside the inner casing 23.
  • Each pipe element 29 is calibrated according to the servitude for which it ensures the connection function.
  • the diameter of the orifice 28 is calibrated according to the pipe element 29 that it receives.
  • each pipe element 29 has a positioning and sealing skirt 31 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 on a thread of the pipe element 29 provided for this purpose, on 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.
  • D ' other intermediate sealing or positioning parts, in particular on the external side of the recess 27, may be provided.
  • connection means 50 make it possible to connect the servitude situated outside the outer casing 24, and for which it is desired to provide a connection with an easement inside the the enclosure defined by the inner housing 23, to the pipe element 29, which has been previously sized to provide this connection.
  • All the pipe elements 29 are fixed in their respective orifice 28.
  • the same number of orifices 28 are provided as pipe elements 29. If this were not the case, the orifices 28 not used would be plugged.
  • the pipe elements 29 comprise a bend 32 near their skirt 31 and extend generally rectilinearly on either side of the bend 32.
  • the pipe elements 29 all have the same shape, except for their diameter, and therefore extend all parallel to each other once mounted.
  • the detachable modular arm 25 of the invention further comprises a profiled liner 33.
  • the liner 33 has a liner body 34 of generally oval section, corresponding to the oval shape of the recess 27, and elongated so as to accommodate the distance separating the inner casing 23 from the outer casing 24.
  • the casing 33 is hollow and open on both sides, and has an outer rim 35, generally perpendicular to the casing body 34, and whose shape corresponds to the shape of the sheet 26 .
  • the oval shape is initially linked to the oval shape that one wishes to give to the liner 33 of the modular arm 35. Indeed, once the turbojet engine is mounted, the liner 33 extends between the inner casing 23 and the outer casing 24, therefore in the secondary flow, its shape to be adapted according to the flow of the secondary flow around it.
  • the oval shape can of course be replaced by any suitable shape.
  • 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 assembly.
  • the rim 35 of the liner 33 is arranged, as we have seen previously, to match the shape of the internal face of the sheet 26, the recess 27 of the sheet being embedded, on the inner side where it projects, into the body 34 of the shirt 33, sized for this purpose.
  • the liner 33 is made integral, by welding or brazing for example, the sheet 26, forming with it and the pipe elements 29, the modular arm 25 of the invention. Once the arm 25 is assembled, the pipe elements 29 protrude, away from the sheet 26, from the enclosure defined by the jacket 33.
  • the inner housing 23 comprises a plurality of longitudinal panel support plates 36, here four in number, which form, with other holding elements such as a ring 37, the frame of the inner housing 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 required surface for enveloping the heart of the turbojet engine 10 and guiding the secondary flow.
  • a plate 39 for receiving a modular arm 25 of easement connection.
  • a plate 39 comprises a longitudinal recess 40, forming a shoulder 41 which follows a generally oval shape corresponding to the section of the inner end of the jacket 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 pipe elements 29 of the modular arm 25 of the invention.
  • Each channel 42 comprises a portion 43 opening on the surface of the recess 40, here with a face perpendicular to this surface, a bend 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, on one or the other lateral longitudinal walls of the support 36. It goes without saying that instead of opening on the side faces of the support 36, the channels 42 could lead to its inner face.
  • Each channel 42 is dimensioned, in its portion 43 opening on the surface of the recess 40, to receive the end of a pipe element 29.
  • the latter may be provided with an O-ring 48 sealing.
  • the ten channels 42 are sized to each receive the 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 to receive a particular modular arm 25: its channels 42 are arranged to receive the pipe elements 29, while the shoulder 41 of the recess 40 is arranged to support the inner end of the body 34 of the jacket 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 inner base 19 of the arms 18 of the intermediate casing 17 and the exhaust casing 21.
  • the servitudes, extending to the inside the chamber which will be defined by the inner casing 23 and intended to be connected with servitudes located outside the outer casing 24, are then connected to the portions 43 of the channels 42 which are intended for them, on the connectors 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 an orifice 49 oval provided for this purpose on the outer casing 24, between the latter and the inner casing 23.
  • the orifice 49 is located directly above the plate 39, so that it is possible, just by inserting the arm 25 in the orifice 49, to come insert the ends of the pipe elements 29 in the portions 43 of pipes 42 of the plate 39 intended to receive them, without the need to access the space defined by the inner housing 23 and the outer casing 24.
  • the plate 26 of the arm 25 is then removably attached to the outer structural casing 24, for example by inserts, or any other suitable means. It could also be soldered, which would however make it more difficult to disassemble the arm 25.
  • the servitudes extending outside the outer casing 24, and to be connected to the aforementioned internal servitudes, can then be connected to the connecting means 50 of the pipe elements 29, the choice obviously being made according to the servitude already connected to each pipe element 29 through the plate 39.
  • the connection of the servitudes between the outer structural casing 24 and the non-structural inner casing 23 is provided, the arm 25, in cooperation with the plate 39 and the orifice 49 of the outer casing. structural 24, allowing the connection of servitudes here.
  • This connection is easily removable and dismountable, without having to disassemble in particular the internal connections made at the side walls of the supports 36.
  • the modular arm 25, its pipe element passage openings 28, the pipe elements 29 and their connections 50, the channels 42 and their connectors 46 are calibrated. depending on the easements they allow to connect. It goes without saying that all of these elements could be calibrated in a standard way, the connectors 46, 50 or other connectors allowing adaptation according to the type and the gauge of the servitudes 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 Entretoise pourvue de raccordements des canalisations de service d'un turboréacteur Active EP1553263B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0400221 2004-01-12
FR0400221A FR2865001B1 (fr) 2004-01-12 2004-01-12 Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes.

Publications (2)

Publication Number Publication Date
EP1553263A1 EP1553263A1 (fr) 2005-07-13
EP1553263B1 true 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 (ja)
EP (1) EP1553263B1 (ja)
JP (1) JP4188323B2 (ja)
CN (1) CN1657757B (ja)
CA (1) CA2492166C (ja)
FR (1) FR2865001B1 (ja)
RU (1) RU2388921C2 (ja)
UA (1) UA85824C2 (ja)

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FR2905975B1 (fr) * 2006-09-20 2008-12-05 Snecma Sa Conduite de soufflante pour une turbomachine.
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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.
FR2919347B1 (fr) * 2007-07-26 2009-11-20 Snecma Enveloppe externe de conduite de soufflante dans une turbomachine.
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
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GB2497809B (en) * 2011-12-22 2014-03-12 Rolls Royce Plc Method of servicing a gas turbine engine
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FR2996070B1 (fr) * 2012-09-21 2018-09-21 Snecma Systeme de guidage de cable dans une veine de turbomachine
WO2014051658A1 (en) 2012-09-26 2014-04-03 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
FR3036437B1 (fr) * 2015-05-22 2017-05-05 Snecma Ensemble de turbomachine pour lubrifier un support de palier
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
FR3097258B1 (fr) * 2019-06-14 2021-07-02 Safran Aircraft Engines Systeme de passage de servitudes a encombrement optimise des servitudes et a montage simplifie
FR3110547B1 (fr) * 2020-05-20 2022-04-22 Safran Nacelles Nacelle pour ensemble propulsif à très grand taux de dilution, comprenant une structure interne avant amovible et structurelle

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Also Published As

Publication number Publication date
RU2388921C2 (ru) 2010-05-10
RU2005100180A (ru) 2006-06-20
EP1553263A1 (fr) 2005-07-13
JP2005201266A (ja) 2005-07-28
US7543442B2 (en) 2009-06-09
CN1657757B (zh) 2011-05-04
CN1657757A (zh) 2005-08-24
JP4188323B2 (ja) 2008-11-26
CA2492166A1 (fr) 2005-07-12
FR2865001A1 (fr) 2005-07-15
UA85824C2 (uk) 2009-03-10
US20050247043A1 (en) 2005-11-10
CA2492166C (fr) 2012-06-19
FR2865001B1 (fr) 2008-05-09

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