EP1553262B1 - Verteilungsträger der Dienstrohre eines Mantelstromtriebwerks - Google Patents

Verteilungsträger der Dienstrohre eines Mantelstromtriebwerks Download PDF

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Publication number
EP1553262B1
EP1553262B1 EP05300012A EP05300012A EP1553262B1 EP 1553262 B1 EP1553262 B1 EP 1553262B1 EP 05300012 A EP05300012 A EP 05300012A EP 05300012 A EP05300012 A EP 05300012A EP 1553262 B1 EP1553262 B1 EP 1553262B1
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EP
European Patent Office
Prior art keywords
ancillaries
turbojet engine
casing
sole plate
support
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
EP05300012A
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English (en)
French (fr)
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EP1553262A1 (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 SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1553262A1 publication Critical patent/EP1553262A1/de
Application granted granted Critical
Publication of EP1553262B1 publication Critical patent/EP1553262B1/de
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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, an air intake shaft, a fan, a compressor, a combustion chamber, a turbine and an exhaust nozzle. These various elements are contained in housings.
  • the turbojet engine further comprises, around these housings, an internal secondary flow casing, in the form of a shell for containing, on its outer surface, the secondary air flow.
  • the secondary air flow corresponds to the air driven by the blower not entering the compressor.
  • This shell comprises opening means in two half-shells, in order to access the heart of the turbojet engine.
  • the elements of the turbojet engine located in the enclosure defined by the internal casing of the secondary flow.
  • Some fluids necessary for the operation of the turbojet engine such as fuel and oil, must be routed from outside the turbojet engine to its core. These fluids are used in particular to supply the combustion chamber with fuel, the various elements of the engine lubricating oil, various cylinders actuating relief valves, variable compressor timing, driving the game of high pressure turbine casings and low pressure, etc.
  • the flow of fluids is carried out by pipes commonly called servitudes.
  • the invention particularly relates to the passage of servitudes along the support arms of a turbojet engine housing, said intermediate.
  • the figure 1 represents a partial view of a turbojet engine 1 of the prior art.
  • the latter comprises, downstream of the fan blade retention casing, the outer shell 2 of a casing, said intermediate, which is traditionally attached to the front suspension of the turbojet engine to an aircraft.
  • the intermediate casing also comprises radial arms 3.
  • Some easements 6 must be routed, from outside the intermediate casing, to the heart of the turbojet engine 1. This routing is generally along an arm 3 of the intermediate casing, the servitudes 6 opening into the heart of the turbojet engine 1 at the level of of the inner ferrule 4.
  • turbojet 1 presented is intended to be mounted on an aircraft whose ground clearance is quite low. His nacelle is flattened in its lower portion and swollen on the sides. For safety reasons, servitudes 6 must not pass in the lower part of turbojet 1, in case of friction on the ground of the latter. They are therefore conveyed along an arm 3 of the intermediate casing spaced from the plane of symmetry - global - vertical turbojet 1.
  • the servitudes 6 pass through the outer shell 2 of the intermediate casing and are contained, between the outer shell 2 and the inner shell 4, in an arm 7, ensuring their protection as well as the guiding of the secondary air flow.
  • the servitudes 6 are fixed, at the level of the inner shell 4, on a sheet 8, by nuts on each side of the sheet 8.
  • the present invention aims to reduce the production costs of the internal casing of the secondary flow, to simplify maintenance of the turbojet and to facilitate access to the heart of the turbojet engine at the passage of servitudes along an arm of the intermediate casing.
  • a turbofan engine comprising an outer casing supported by arms, an inner casing to the right of the outer casing and servitudes is characterized in that, in the axis of an arm, is provided on the inner casing, a support receiving servitudes having, on the outer side of the inner casing, a first sole for receiving servitudes.
  • Axis here means the axis or direction of the gas flow around the arm.
  • the first sole comprises service receiving channels.
  • the service distribution support comprises, on the internal side of the inner casing, a second sole for the distribution of servitudes.
  • the service receiving channels open on the second flange, which comprises servitude connectors.
  • the outer casing comprises a set of easement passage.
  • the easement passage assembly comprises a fastening flange, supporting a seal, and an attached bearing sector.
  • the seal is of elastomeric material and comprises service passage channels.
  • the turbojet comprises a service protection arm mounted between the easement passage assembly and the service distribution support.
  • the invention is particularly applicable to an outer casing which is the outer shell of the intermediate casing of a turbojet, and to an inner casing which is the inner shell of the intermediate casing, but the applicant does not intend to limit the scope of its rights to this application.
  • the invention further relates, as an intermediate product, a service distribution support for the turbojet engine presented above, comprising a first sole for receiving easements and a second sole for the distribution of easements.
  • the facility receiving plate comprises service receiving channels.
  • the channels open on the distribution base, which comprises at their point of uncoupling servitude connectors.
  • the turbojet engine 10 of the invention comprises, downstream of the fan blade retaining casing, a casing said intermediate casing, which is traditionally attached to the front suspension of the turbojet engine 10 to an aircraft;
  • the intermediate casing comprises an 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 conveyance of servitudes along a radial arm 12 of the intermediate casing.
  • the intermediate casing 11 On the intermediate casing 11, to the right of the shell 34, is drilled, from the downstream edge 14 of the intermediate casing 11, a recess 13 generally rectangular.
  • the intermediate casing 11 comprises, along the circumference of its downstream edge 14, a channel 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 part 16 which will be named attached support sector 16.
  • the flange 14 is generally in the form of a metal stirrup, comprising a base 17 and two branches 20, 20 ', slightly curved to fit the shape of the intermediate casing 11.
  • the base 17 of the flange 14 is arranged to bear 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 inner side of the base 17.
  • the shoulder 18 is shaped to bear on the inner face of the intermediate casing 11, upstream of the recess 13.
  • the flange 14 Between the branches 20, 20 'of the flange 14, on its external side, is mounted a seal 15, here elastomeric material, whose outer surface is at the same level as the outer surface of the flange 14.
  • the elastomer seal 15 is pierced with a plurality of radial channels 25 for the passage of easements.
  • the flange 14 At its downstream end, the flange 14 comprises, at each of its branches 20, 20 ', a longitudinal shoulder 21, 21', situated at a distance of the outer surface of the flange is smaller than that of the opposite shoulder 18.
  • the joint support sector 16 is in the form of a metal plate. It comprises, on its downstream edge, two radial projections 26, 26 'forming a channel 27, arranged to ensure the continuity of the channel 28 of the intermediate casing 11.
  • the joint support sector 16 On its upstream edge, the joint support sector 16 comprises a central radial projection 29 having at its outer end two longitudinal fingers 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 elastomer seal 15.
  • the joint bearing sector 16 further comprises, on its upstream edge, on either side of the central projection 29, two radial bores 32, 32 'for receiving screws 33, 33', spaced apart from each other. other the same distance as the bores 22, 22 'of the flange 14.
  • the mounting of the flange 14, on which the elastomer seal 15 is arranged, and the joint bearing sector 16 in the recess 13 is as follows.
  • 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 bearing on the inner face of the intermediate casing 11, upstream of the recess 13.
  • the lugs 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 attached bearing sector 16.
  • the flange 14, the elastomeric seal 15 and the attached support sector 16 ensure the continuity of the intermediate casing 11, while providing channels 25 of easement passage. They constitute a set of passage of servitudes 53, which makes it possible to ensure the passage of the servitudes through the intermediate casing 11, while tightening them relative to each other, according to the distribution of the channels 25 on the elastomer seal 15. It furthermore ensures the tightness of the assembly, the constraints being forcibly inserted into their channels 25.
  • a service distribution support 35 placed at the right of the easement passage assembly 53.
  • the support 35 comprises, on the outer side of the ferrule 34, a first sole for receiving servitudes 36 projecting out of the latter.
  • the sole 36 has a rounded triangular shape, the base of which is located on the upstream side of the shell 34, at the level of the arm 12, and the top of the downstream side of the shell 34.
  • the width of the base corresponding approximately to the transverse width of the arm 12.
  • the first flange 36 comprises service receiving channels 37, opening on its outer surface.
  • the end of the servitudes 38 comprises a specific tip, composed of an annular seal 40, comprising an annular groove 41.
  • the seal 40 is adapted to its receiving channel 37, and is fitted so that its groove 41 is flush with on the surface of the first flange 36.
  • Metal plates 42, including adapted recesses 43, are fixed, using screws 44, on the sole 36, their recesses 43 engaging on the grooves 41 of the seals 40 of the easements 38 to block the latter in radial translation.
  • an arm 45 for the protection of servitudes is fastened to the sole 36, to the radial support 39, to the flange 14 and to the attached bearing sector 16.
  • This arm 45 is in the form of a metal sheet that adapts to the set of elements to which it is attached, in order to protect the whole. Its section is generally constant and corresponds to the contour of the sole plate 36. It is arranged to complete the shape of the arm in order to guide the flow of secondary air 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 service distribution support 35 comprises, on the internal side of the shell, a second sole plate 46 of service distribution, located at the right of the first sole plate 36.
  • the reception channels 37 of the servitudes 38 pass through the first sole plate 36, external, and extend into the second distribution sole 46. In the latter, they can be oriented, by a bend 47, so as to lead to a side face of the second sole 46, or not to change direction and lead to the inner face of the second sole 46. They can further change diameter if desired.
  • ком ⁇ онент connectors 48 At the open end of the channels 37, on the second flange 46, are arranged servitude connectors 48. These connectors 48 comprise a connector gasket 49, a nozzle 50 and a nut 51 for screwing an easement. Thus, it is possible to connect servitudes 52, provided with ends arranged for this purpose, to the service connections 48 of the second flange 46.
  • the passage of the servitudes 38 between the intermediate casing 11 and the ferrule 34 is ensured.
  • the servitudes 38 are inserted in the channels 25 of the elastomer seal 15, extend in the chamber formed by the arm 45 and the radial support 39, between the intermediate casing 11 and the ferrule 34, and are inserted into the channels 37 of the service distribution support 35, by their tips 40 adapted for this purpose, at which they are blocked in radial translation by the metal plates 42.
  • the channels 37 provide the link with the servitudes 52 of the interior of the shell 34, that is to say, the heart of the turbojet engine 10, which are connected to them by the connectors 48 of the distribution plate 46.
  • the channels 25 of the elastomeric seal 15, the channels 37 of the service distribution support 35, the metal plates 42 and the connectors 48 of the second base 46 are dimensioned and shaped according to the easements 38, 52 that they must connect.
  • the assembly of the latter is, thanks to the invention, perfectly simplified and standardized.
  • the service distribution support 35 can indifferently be formed in one piece with the ferrule 34 or attached thereto.

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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)

Claims (14)

  1. Mantelstromtriebwerk, das ein von Armen (12) getragenes Außengehäuse (11), ein Innengehäuse (34) am Außengehäuse (11) und Versorgungsvorrichtungen (38, 52) aufweist, dadurch gekennzeichnet, dass an der Achse eines Armes (12) auf dem Innengehäuse (34) ein Verteilungsträger für die Versorgungsvorrichtungen (35) angebracht ist, der an der Außenseite des Innengehäuses (34) einen ersten Standfuß (36) für die Aufnahme der Versorgungsvorrichtungen aufweist.
  2. Mantelstromtriebwerk nach Anspruch 1, wobei der erste Standfuß (36) Aufnahmekanäle (37) für die Versorgungsvorrichtungen aufweist.
  3. Mantelstromtriebwerk nach einem der Ansprüche 1 bis 2, wobei der Verteilungsträger (35) für die Versorgungsvorrichtungen auf der Innenseite des Innengehäuses (34) einen zweiten Standfuß (46) für die Verteilung der Versorgungsvorrichtungen aufweist.
  4. Mantelstromtriebwerk nach den Ansprüchen 2 und 3, wobei die Aufnahmekanäle (37) für die Versorgungsvorrichtungen in den zweiten Standfuß (46) münden, der Verbindungselemente (48) für die Versorgungseinrichtungen aufweist.
  5. Mantelstromtriebwerk nach einem der Ansprüche 1 bis 4, wobei das Außengehäuse (11) eine Durchgangseinheit (53) für die Versorgungsvorrichtungen aufweist.
  6. Mantelstromtriebwerk nach Anspruch 5, wobei die Durchgangseinheit (53) für die Versorgungsvorrichtungen eine Befestigungsklammer (14), die ein Verbindungsstück (15) hält, und einen Verbindungsstückauflagebereich (16) aufweist.
  7. Mantelstromtriebwerk nach Anspruch 6, wobei das Verbindungsstück (15) Durchgangskanäle (25) für die Versorgungsvorrichtungen aufweist.
  8. Mantelstromtriebwerk nach Anspruch 7, wobei das Verbindungsstück (15) aus Elastomermaterial ist.
  9. Mantelstromtriebwerk nach einem der Ansprüche 5 bis 8, das einen zwischen der Durchgangseinheit (53) für die Versorgungsvorrichtungen und dem Verteilungsträger (35) für die Versorgungsvorrichtungen angebrachten Schutzarm (45) für die Versorgungsvorrichtungen aufweist.
  10. Mantelstromtriebwerk nach einem der Ansprüche 1 bis 9, wobei das Außengehäuse der Außenmantel des Mittelgehäuses (11) ist und das Innengehäuse der Innenmantel des Mittelgehäuses (34) ist.
  11. Verteilungsträger für Versorgungsvorrichtungen für das Mantelstromtriebwerk aus Anspruch 1, der einen ersten Standfuß (36) für die Aufnahme der Versorgungsvorrichtungen und einen zweiten Standfuß (46) für die Verteilung der Versorgungsvorrichtungen aufweist.
  12. Verteilungsträger für Versorgungsvorrichtungen nach Anspruch 11, wobei der erste Standfuß (36) Aufnahmekanäle (37) für die Versorgungsvorrichtungen aufweist.
  13. Verteilungsträger für Versorgungsvorrichtungen nach Anspruch 12, wobei auf dem ersten Standfuß (36) Metallplatten (42) zum Blockieren der Verschiebung der Versorgungsvorrichtungen angeordnet sind.
  14. Verteilungsträger für Versorgungsvorrichtungen nach einem der Ansprüche 12 oder 13, wobei die Kanäle (37) in den zweiten Standfuß (46) münden, der Verbindungselemente (48) für die Versorgungseinrichtungen aufweist.
EP05300012A 2004-01-12 2005-01-11 Verteilungsträger der Dienstrohre eines Mantelstromtriebwerks Active EP1553262B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
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.
FR0400222 2004-01-12

Publications (2)

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

Family

ID=34586488

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05300012A Active 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)

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FR2925120B1 (fr) * 2007-12-18 2010-02-19 Snecma Extension de carter intermediaire pour turboreacteur d'aeronef, comprenant une rainure annulaire sectorisee de reception des capots de nacelle
FR2928961B1 (fr) * 2008-03-19 2015-11-13 Snecma Distributeur sectorise pour une turbomachine.
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FR2999651B1 (fr) 2012-12-18 2015-01-16 Snecma Extension de carter intermediaire a conception amelioree
FR3005992B1 (fr) * 2013-05-24 2015-05-22 Snecma Dispositif de passage de servitudes pour une turbomachine
FR3011584B1 (fr) * 2013-10-04 2018-02-23 Safran Aircraft Engines Extension de carter intermediaire
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
US10641115B2 (en) * 2017-08-29 2020-05-05 United Technologies Corporation Segmented conduit with airfoil geometry
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
FR3086003B1 (fr) * 2018-09-17 2020-12-25 Safran Aircraft Engines Systeme de distribution d'un fluide primaire et d'un fluide secondaire
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Also Published As

Publication number Publication date
RU2005100179A (ru) 2006-06-20
FR2865002A1 (fr) 2005-07-15
ES2315820T3 (es) 2009-04-01
JP2005201267A (ja) 2005-07-28
CA2492171A1 (fr) 2005-07-12
CA2492171C (fr) 2012-05-01
EP1553262A1 (de) 2005-07-13
UA84680C2 (ru) 2008-11-25
US7506499B2 (en) 2009-03-24
US20050247042A1 (en) 2005-11-10
RU2365777C2 (ru) 2009-08-27
CN100447397C (zh) 2008-12-31
FR2865002B1 (fr) 2006-05-05
JP4081090B2 (ja) 2008-04-23
CN1661201A (zh) 2005-08-31
DE602005009982D1 (de) 2008-11-13

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