EP1553262A1 - Verteilungsträger der Dienstrohre eines Mantelstromtriebwerks - Google Patents

Verteilungsträger der Dienstrohre eines Mantelstromtriebwerks Download PDF

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Publication number
EP1553262A1
EP1553262A1 EP05300012A EP05300012A EP1553262A1 EP 1553262 A1 EP1553262 A1 EP 1553262A1 EP 05300012 A EP05300012 A EP 05300012A EP 05300012 A EP05300012 A EP 05300012A EP 1553262 A1 EP1553262 A1 EP 1553262A1
Authority
EP
European Patent Office
Prior art keywords
easements
casing
turbojet engine
service
sole
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
EP05300012A
Other languages
English (en)
French (fr)
Other versions
EP1553262B1 (de
Inventor
Jérémy Fert
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 EP1553262A1 publication Critical patent/EP1553262A1/de
Application granted granted Critical
Publication of EP1553262B1 publication Critical patent/EP1553262B1/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.
  • 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 crankcases.
  • the turbojet engine further comprises, around these housings, a crankcase internal secondary flow, in the form of a hull to contain, on its outer surface, the secondary air flow.
  • the secondary air flow corresponds to the air driven by the fan does not not penetrating into the compressor.
  • This hull includes means opening in two half-shells, in order to access the heart of the turbojet.
  • heart of the turbojet we mean the elements of the turbojet engine located in the enclosure defined by the inner casing of the flow secondary.
  • Some fluids necessary for the operation of the turbojet such as fuel and oil, must be brought from outside the turbojet to his heart. These fluids serve in particular to feed the fuel combustion chamber, the various elements of the engine in lubricating oil, various actuating cylinders of discharge valves, Variable compressor timing, piloting the clearance of the turbine housings high pressure and low pressure, etc.
  • the routing of the fluids is carried out by pipelines commonly called easements.
  • the invention is particularly the passage of easements along the support arms of a crankcase turbojet, says intermediate.
  • FIG. 1 represents a partial view of a turbojet engine 1 of the art prior.
  • the latter comprises, downstream of the retention casing of the blades of blower, the outer shell 2 of a housing, said intermediate, which is traditionally fixed the front suspension of the turbojet engine to an airplane.
  • the intermediate casing also comprises radial arms 3.
  • an inner shell 4 At the right of its outer shell 2, is arranged an inner shell 4, this inner shell 4 comprising a bearing shoulder 5 of the internal casing of the secondary flow, not shown.
  • Some easements 6 must be brought from the outside of the intermediate casing, towards the heart of the turbojet engine 1. This routing is generally done along an arm 3 of the intermediate casing, the easements 6 opening into the heart of the turbojet 1 at the level of the inner ferrule 4.
  • the turbojet 1 presented is intended to be mounted on an airplane whose ground clearance is quite low. His nacelle is flattened in his lower portion and swollen on the sides. For security reasons, servitudes must not pass through the lower part of turbojet 1, case of friction on the ground of the latter. They are therefore transported on along an arm 3 of the intermediate casing spaced apart from the plane of symmetry - overall vertical of the turbojet engine 1.
  • the easements 6 pass through the outer shell 2 of the housing intermediate and are contained between the outer shell 2 and the inner ferrule 4, in an arm 7, ensuring their protection and guiding the air flow secondary.
  • the easements 6 are fixed at the inner ferrule 4, on a sheet 8, by nuts on each side of the sheet 8.
  • the present invention aims at reducing the production costs of the internal casing of the secondary flow, to simplify the maintenance of the turbojet engine and to facilitate access to the heart of the turbojet engine at the passage of easements along an arm of the intermediate casing.
  • a turbofan engine comprising an outer casing supported by arms, an internal casing right of the outer casing and easements is characterized by the fact that in the axis of an arm, is formed, on the inner casing, a receiving support of servitudes comprising, on the external side of the inner casing, a first sole for receiving easements.
  • axis here means the axis or direction of the gas flow around the arms.
  • the first sole has channels of reception of easements.
  • the service distribution support comprises, on the inner side of the inner casing, a second sole for the distribution of easements.
  • the reception channels of easements open onto the second flange, which has fittings easements.
  • the housing external includes a set of easements.
  • the easement crossing assembly comprises a fixing flange, supporting a seal, and an attached bearing area.
  • the seal is of elastomeric material and includes channels of passage of easements.
  • the turbojet engine comprises a protective arm of easements mounted between the easement passage assembly and the support distribution of easements.
  • the invention is particularly applicable to an external casing which is the outer shell of the intermediate casing of a turbojet engine, and a crankcase internal which is the inner shell of the intermediate casing, but the plaintiff does not intend to limit the scope of his rights to this application.
  • the invention also concerns, as an intermediate product, a servitude distribution support for the turbojet engine presented above, having a first sole for receiving easements and a second sole for the distribution of easements.
  • the platform for receiving servitudes comprises service receiving channels.
  • the channels open on the sole of distribution system, which includes at its point of easements.
  • the turbojet engine 10 of the invention comprises, downstream of the fan blade retention casing, a casing intermediate housing, which is traditionally attached to the suspension before the turbojet engine 10 to an airplane;
  • the intermediate casing has a outer shell 11, supported radial arms 12, at the foot of which extends, on the downstream side, an inner shell 34, to the right of the outer shell 11.
  • the invention particularly relates to the routing of easements along a radial arm 12 of the intermediate casing.
  • the intermediate casing 11 On the intermediate casing 11, to the right of the ferrule 34, is pierced, from the downstream edge 14 of the intermediate casing 11, a recess 13 globally rectangular.
  • the intermediate casing 11 comprises, along the circumference of its downstream edge 14, a gutter 28.
  • the recess 13 is arranged to receive a set of easement passage 53, comprising a fastening flange 14, supporting a seal 15 for guiding and clamping servitudes, and a piece 16 which will be named attached support sector 16.
  • turbojet engine of the invention will be described, in the rest of the description, in the reference of the turbojet engine. So, when the pieces will be represented, in a figure, not mounted on the turbojet engine, we will designate their various portions according to their placement once mounted. It is in the reference of the turbojet, particular in terms of its axis, that it will be necessary to understand the various qualifiers such as internal, external, radial, axial, longitudinal, upstream, downstream, ...
  • the flange 14 is generally under the shape of a metal stirrup, comprising a base 17 and two branches 20, 20 ', slightly curved to fit the crankcase shape intermediate 11.
  • the base 17 of the flange 14 is arranged to come in support on the upstream bottom 19 of the recess 13 of the intermediate casing 11. It comprises a longitudinal shoulder 18 whose projecting portion is on the side internal of the base 17.
  • the shoulder 18 is shaped to come into support on the inner face of the intermediate casing 11, upstream of the recess 13.
  • the elastomeric seal 15 is pierced with a plurality of radial channels 25 easement passage.
  • the flange 14 comprises, at the level of each of its branches 20, 20 ', a longitudinal shoulder 21, 21', located at a distance of the outer surface of the flange is smaller than that of the opposite shoulder 18.
  • the joint support sector 16 presents itself in the form of a metal plate. It comprises, on its downstream edge, two radial projections 26, 26 'forming a gutter 27, arranged to ensure the continuity of the gutter 28 of the intermediate casing 11.
  • the attached support sector 16 On its upstream edge, the attached support sector 16 has a protrusion radial central 29 having at its outer end two fingers longitudinal 30, 30 ', extending upstream.
  • the upstream face 31 of the projection 29 and its fingers 30, 30 ' are shaped to bear on the downstream face and the outer face, respectively, of the elastomeric seal 15.
  • the attached support sector 16 further comprises, on its upstream edge, on either side of the central projection 29, two radial bores 32, 32 'of receiving screws 33, 33 'spaced from each other by the same distance as the bores 22, 22 'of the flange 14.
  • the mounting of the flange 14, on which is arranged the seal elastomer 15, and the attached bearing sector 16 in the recess 13 is the next.
  • the flange 14 is mounted in the recess 13, with its base 17 bearing on the upstream bottom 19 of the recess 13 and its shoulder 18 in bearing on the inner face of the intermediate casing 11, upstream of the recess 13.
  • the ears 23, 23 ' are in contact with the inner face of the intermediate casing 11, fixed to the latter by screws in their bores 24, 24 '.
  • the joint support sector 16 is fixed to the flange 14 by the screws 33, 33 ' in the bores 22, 22 'of the flange 14 through the bores 32, 32' of the joint bearing sector 16.
  • the flange 14, the elastomer seal 15 and the sector support 16 ensure the continuity of the intermediate casing 11, while providing channels for the passage of easements. They constitute a set of passage of easements 53, which ensures the passage of servitudes through the intermediate casing 11, while tightening the relative to each other, according to the distribution of the channels 25 on the joint elastomer 15. It also ensures the tightness of the assembly, easements being inserted by force into their channels 25.
  • a service distribution support 35 placed at the right of the crossing set of easements 53.
  • the support 35 comprises, on the outer side of the shell 34, a first outsole for the receipt of easements 36 protruding out of the latter.
  • the sole 36 has a rounded triangular shape, the base of which is on the upstream side of ferrule 34, at arm 12, and the top on the downstream side of ferrule 34.
  • the width of the base corresponding to approximately the transverse width of the arm 12.
  • the first sole 36 comprises service receiving channels 37, opening on its outer surface.
  • Easements 38 coming from outside the intermediate casing 11, are inserted into the channels 25 of the elastomer seal 15, extend the along a radial support 39 parallel to the arm 12 mounted between the housing intermediate 11 and the ferrule 34, and their end is fitted into the channels 37 of the sole 36.
  • the end of the servitudes 38 comprises a specific tip, composed of an annular seal 40, comprising a annular groove 41.
  • the seal 40 is adapted to its receiving channel 37, and is fitted so that its groove 41 is flush with the surface of the first sole 36.
  • Metal plates 42 comprising adapted recesses 43, are fixed, using screws 44, on the sole 36, their recesses 43 engaging on the grooves 41 of the joints 40 of the easements 38 to block the latter in radial translation.
  • an arm 45 for the protection of servitudes is attached to the sole 36, to the radial support 39, to the flange 14 and to the bearing sector 16.
  • This arm 45 is in the form of a sheet adapting to all the elements to which it is attached, in order to protect the whole. Its section is globally constant and corresponds to the contour of the sole 36. It is arranged to complete the shape of the arm for the purpose of guiding the secondary air flow flowing between the intermediate casing 11 and the ferrule 34. This form is adapted to the dynamic stresses that are imposed on the flow, and proceeds from parameters mainly related to fluid mechanics.
  • the distribution support of servitudes 35 comprises, on the inner side of the ferrule, a second sole 46 distribution of easements, located at the right of the first sole 36.
  • the reception channels 37 of the easements 38 pass through the first sole 36, external, and extend into the second sole of distribution 46. In the latter, they can be oriented, by an elbow 47, so as to open on a lateral face of the second sole 46, or do not change direction and lead to the inner face of the second sole 46. They can further change diameter if this is longed for.
  • Arrangements 48 are provided at the open end of the channels 37, on the second flange 46. These connectors 48 comprise a connecting joint 49, a nozzle 50 and a nut 51 for screwing an easement. Thus, it is possible to connect servitudes 52, provided with end caps arranged for this purpose, at the service connections 48 of the second sole 46.
  • the channels 25 of the elastomer seal 15, the channels 37 of the support of distribution of easements 35, metal plates 42 and connectors 48 of the second sole 46 are dimensioned and shaped according to the easements 38, 52 that they must connect.
  • the assembly of these is therefore, thanks to the invention, perfectly simplified and standardized.
  • easements 38, 52 are not more fixed by nuts on both sides of the shell 34 but fitted into channels 37 or end-pieces 48, saving space for their connection is large, and allows to obtain a distribution support of easements 35 whose longitudinal surface does not extend beyond that of ferrule 34. It is therefore no longer necessary to practice a recess in the covers of the internal casing of the secondary flow, since the arm 45, located at right of the service distribution support 35 and in particular of its first sole 36, does not encroach on their opening zone and closing.
  • the service distribution support 35 can indifferently be formed in one piece with the ferrule 34 or reported on the latter.

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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)
  • Automatic Cycles, And Cycles In General (AREA)
EP05300012A 2004-01-12 2005-01-11 Verteilungsträger der Dienstrohre eines Mantelstromtriebwerks Expired - Lifetime EP1553262B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0400222 2004-01-12
FR0400222A FR2865002B1 (fr) 2004-01-12 2004-01-12 Turboreacteur a double flux comprenant un support de distribution de servitudes et le support de distribution de servitudes.

Publications (2)

Publication Number Publication Date
EP1553262A1 true EP1553262A1 (de) 2005-07-13
EP1553262B1 EP1553262B1 (de) 2008-10-01

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP05300012A Expired - Lifetime EP1553262B1 (de) 2004-01-12 2005-01-11 Verteilungsträger der Dienstrohre eines Mantelstromtriebwerks

Country Status (10)

Country Link
US (1) US7506499B2 (de)
EP (1) EP1553262B1 (de)
JP (1) JP4081090B2 (de)
CN (1) CN100447397C (de)
CA (1) CA2492171C (de)
DE (1) DE602005009982D1 (de)
ES (1) ES2315820T3 (de)
FR (1) FR2865002B1 (de)
RU (1) RU2365777C2 (de)
UA (1) UA84680C2 (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2925120A1 (fr) * 2007-12-18 2009-06-19 Snecma Sa Extension de carter intermediaire pour turboreacteur d'aeronef, comprenant une rainure annulaire sectorisee de reception des capots de nacelle
WO2014188122A1 (fr) * 2013-05-24 2014-11-27 Snecma Dispositif de passage de servitudes pour une turbomachine
FR3011584A1 (fr) * 2013-10-04 2015-04-10 Snecma Extension de carter intermediaire
EP3450696A1 (de) * 2017-08-29 2019-03-06 United Technologies Corporation Segmentierter kanal mit tragflächengeometrie
FR3086003A1 (fr) * 2018-09-17 2020-03-20 Safran Aircraft Engines Systeme de distribution d'un fluide primaire et d'un fluide secondaire
FR3123942A1 (fr) * 2021-06-09 2022-12-16 Safran Aircraft Engines Support de carenage incurvé d’un bras structural de turbomachine

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WO2004011521A1 (ja) * 2002-07-29 2004-02-05 Sumitomo Chemical Company, Limited 熱硬化性樹脂組成物及び接着性フィルム
US20060032974A1 (en) * 2004-08-16 2006-02-16 Honeywell International Inc. Modular installation kit for auxiliary power unit
FR2875855B1 (fr) * 2004-09-27 2006-12-22 Snecma Moteurs Sa Turboreacteur avec un bras monobloc de raccord de servitudes et le bras monobloc de raccord de servitudes
FR2920195B1 (fr) * 2007-08-23 2009-11-20 Snecma Turbomachine a double flux a reduction de bruit de jet
FR2928961B1 (fr) * 2008-03-19 2015-11-13 Snecma Distributeur sectorise pour une turbomachine.
FR2930592B1 (fr) * 2008-04-24 2010-04-30 Snecma Distributeur de turbine pour une turbomachine
US20100238270A1 (en) * 2009-03-20 2010-09-23 Intrepid Management Group, Inc. Endoscopic apparatus and method for producing via a holographic optical element an autostereoscopic 3-d image
US8753075B2 (en) * 2010-07-20 2014-06-17 Rolls-Royce Corporation Fan case assembly and method
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
GB2498006B (en) 2011-12-22 2014-07-09 Rolls Royce Plc Gas turbine engine systems
US10087847B2 (en) 2012-09-26 2018-10-02 United Technologies Corporation Seal assembly for a static structure of a gas turbine engine
FR2999651B1 (fr) * 2012-12-18 2015-01-16 Snecma Extension de carter intermediaire a conception amelioree
FR3015625B1 (fr) * 2013-12-20 2015-12-11 Snecma Bras de guidage d'elements de forme allongee, en particulier pour une turbomachine
FR3034465B1 (fr) * 2015-04-03 2017-05-05 Snecma Turbomoteur comportant deux flux de ventilation distincts
CN105715316B (zh) * 2016-01-26 2017-06-27 北京航空航天大学 一种带倒z字形支板的简易排气框架
FR3051840B1 (fr) * 2016-05-31 2020-01-10 Safran Aircraft Engines Carter intermediaire de turbomachine, equipee d'une piece d'etancheite a interface bras/virole
DE102016215030A1 (de) * 2016-08-11 2018-02-15 Rolls-Royce Deutschland Ltd & Co Kg Turbofan-Triebwerk mit einer im Sekundärstromkanal liegenden und ein separates Abschlusselement aufweisenden Verkleidung
RU2642991C1 (ru) * 2017-04-19 2018-01-29 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Клапанный узел канала перепуска компрессора
US10800536B2 (en) * 2017-06-09 2020-10-13 General Electric Company Propulsion system for an aircraft
FR3077846B1 (fr) * 2018-02-14 2020-03-13 Safran Aircraft Engines Virole exterieure de carter intermediaire pour turbomachine d'aeronef a double flux, comprenant des dispositifs ameliores d'etancheite a l'air et de resistance au feu

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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 (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

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2925120A1 (fr) * 2007-12-18 2009-06-19 Snecma Sa Extension de carter intermediaire pour turboreacteur d'aeronef, comprenant une rainure annulaire sectorisee de reception des capots de nacelle
US8172527B2 (en) 2007-12-18 2012-05-08 Snecma Intermediate casing extension for an aircraft jet engine, comprising a sectorised annular groove for receiving the nacelle covers
EP2072397A3 (de) * 2007-12-18 2013-03-06 Snecma Verlängerung des Zwischengehäuses für ein Flugzeugturbinentriebwerk, die eine in Sektoren unterteilte Ringnut zur Aufnahme der Triebwerksverkleidung umfasst
WO2014188122A1 (fr) * 2013-05-24 2014-11-27 Snecma Dispositif de passage de servitudes pour une turbomachine
FR3005992A1 (fr) * 2013-05-24 2014-11-28 Snecma Dispositif de passage de servitudes pour une turbomachine
GB2528824A (en) * 2013-05-24 2016-02-03 Snecma Turbomachine auxiliary lead-through device
GB2528824B (en) * 2013-05-24 2018-01-10 Snecma Turbomachine auxiliary lead-through device
FR3011584A1 (fr) * 2013-10-04 2015-04-10 Snecma Extension de carter intermediaire
EP3450696A1 (de) * 2017-08-29 2019-03-06 United Technologies Corporation Segmentierter kanal mit tragflächengeometrie
US10641115B2 (en) 2017-08-29 2020-05-05 United Technologies Corporation Segmented conduit with airfoil geometry
FR3086003A1 (fr) * 2018-09-17 2020-03-20 Safran Aircraft Engines Systeme de distribution d'un fluide primaire et d'un fluide secondaire
FR3123942A1 (fr) * 2021-06-09 2022-12-16 Safran Aircraft Engines Support de carenage incurvé d’un bras structural de turbomachine

Also Published As

Publication number Publication date
JP2005201267A (ja) 2005-07-28
UA84680C2 (ru) 2008-11-25
CA2492171A1 (fr) 2005-07-12
CA2492171C (fr) 2012-05-01
RU2005100179A (ru) 2006-06-20
US20050247042A1 (en) 2005-11-10
US7506499B2 (en) 2009-03-24
CN1661201A (zh) 2005-08-31
DE602005009982D1 (de) 2008-11-13
FR2865002A1 (fr) 2005-07-15
JP4081090B2 (ja) 2008-04-23
EP1553262B1 (de) 2008-10-01
FR2865002B1 (fr) 2006-05-05
ES2315820T3 (es) 2009-04-01
RU2365777C2 (ru) 2009-08-27
CN100447397C (zh) 2008-12-31

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