EP2071142A1 - Dichtigkeit eines Nabenhohlraums eines Austrittsgehäuses in einem Turbotriebwerk - Google Patents

Dichtigkeit eines Nabenhohlraums eines Austrittsgehäuses in einem Turbotriebwerk Download PDF

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Publication number
EP2071142A1
EP2071142A1 EP08168877A EP08168877A EP2071142A1 EP 2071142 A1 EP2071142 A1 EP 2071142A1 EP 08168877 A EP08168877 A EP 08168877A EP 08168877 A EP08168877 A EP 08168877A EP 2071142 A1 EP2071142 A1 EP 2071142A1
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EP
European Patent Office
Prior art keywords
radial
casing
wall
cylindrical
exhaust casing
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
EP08168877A
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English (en)
French (fr)
Other versions
EP2071142B1 (de
Inventor
Xavier Firmin Camille Jean Lescure
Aurélien René-Pierre Massot
Sebastien Jean Laurent Prestel
Christian René Schnell
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 EP2071142A1 publication Critical patent/EP2071142A1/de
Application granted granted Critical
Publication of EP2071142B1 publication Critical patent/EP2071142B1/de
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Anticipated expiration legal-status Critical

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the present invention relates to an exhaust casing in a turbomachine, such as an aircraft turbojet, and relates more particularly to the sealing of a hub cavity in the exhaust casing.
  • the exhaust casing of a turbomachine is mounted downstream of a turbine and generally comprises two coaxial cylindrical walls, respectively radially inner and outer, which are connected by radial arms, the inner wall being surrounded by a cylindrical envelope intended to guiding an exhaust stream from the turbine.
  • the cylindrical envelope is fixed by its downstream end to the inner wall of the exhaust casing, and comprises at its upstream end a radial annular portion extending freely towards the axis of the turbomachine so that the inner wall of the casing exhaust and the cylindrical envelope delimit a cavity, commonly called hub cavity.
  • This cavity is open at the inner end of the radial annular portion of the cylindrical envelope.
  • the cylindrical envelope has vibration modes substantially corresponding to the frequencies of the rotor or rotors of the turbomachine, and is therefore likely to resonate with the rotor or rotors, thereby generating strong vibrations likely to penalize the life of the cylindrical envelope.
  • the invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the disadvantages of the known technique.
  • turbomachine exhaust casing comprising two coaxial cylindrical walls, respectively radially inner and radially outer, connected by radial arms, and a cylindrical envelope integral with the downstream end of the radially inner wall and which delimits a hub cavity with the radially inner wall and an exhaust gas flow space with the radially outer wall, the cylindrical shell having at its upstream end a radial annular portion extending towards the axis of the turbomachine, characterized in that the radial annular portion of the casing has at its inner end an annular flange cooperating by substantially radially sliding radial sealing with the inner cylindrical wall of the exhaust casing.
  • the annular flange of the radial portion of the cylindrical casing makes it possible to prevent the circulation of air in the hub cavity.
  • This radially sliding connection mode makes it possible to ensure a good seal of the hub cavity while avoiding the appearance of mechanical stresses in the cylindrical envelope due to the expansions. thermal conditions that may occur at operating temperatures of the turbomachine.
  • the axial retention of the upstream end of the cylindrical envelope makes it possible to raise the frequencies of the vibration modes of the envelope and thus to avoid the resonance phenomena, for example with the rotor of the turbomachine, which are detrimental to its behavior over time.
  • the inner wall of the exhaust casing comprises two annular flanges, respectively upstream and downstream, extending radially outwards and disposed facing each other so as to form an annular groove for receiving the annular flange of the cylindrical envelope with an axial clearance for a substantially sealed connection of the cylindrical envelope to the radially inner wall allowing a radial displacement of the annular flange of the envelope.
  • the two flanges of the inner wall of the exhaust casing have a radial dimension greater than a maximum allowable amplitude of a radial displacement of the annular flange of the cylindrical envelope caused by an expansion. thermal of the latter.
  • the annular flange of the cylindrical envelope is not likely to disengage from the annular groove formed by the two flanges of the inner wall of the exhaust casing under the effect of thermal expansion, at least as long as the radial displacement of the annular flange does not exceed a maximum value corresponding to a predetermined maximum temperature that the cylindrical envelope is not likely to exceed during normal operation of the turbomachine.
  • the annular flange of the cylindrical envelope preferably extends substantially to the bottom of the annular groove of the inner wall of the exhaust casing in stopping condition of the turbomachine.
  • the cylindrical envelope is elastically preloaded, under stopping condition of the turbomachine, so as to apply the upstream face of the annular flange of its radial annular portion against the upstream annular flange of the inner wall. exhaust housing, to seal the hub cavity.
  • the cylindrical envelope is elastically prestressed, in the stopping condition of the turbomachine, so as to apply the downstream face of the annular flange of its radial annular part against the annular flange downstream of the internal wall of the exhaust casing, to seal the hub cavity.
  • the annular flange of the radial annular portion of the cylindrical envelope preferably comprises at its radially outer end a cylindrical flange extending upstream and forming a radial bearing abutment on the upstream annular flange of the inner wall of the housing. exhaust.
  • the radial annular portion of the cylindrical envelope comprises orifices for the passage of a flow of fresh air.
  • This embodiment is well suited to the case where the hub cavity requires to be ventilated.
  • the size of the orifices can then be chosen according to the level of ventilation required and allows the ventilation air flow rate to be controlled.
  • the invention also relates to a cylindrical envelope for a turbomachine of the type described above, comprising at one of its an annular flange and at the other end thereof an inwardly extending radial annular portion, characterized in that the radial annular portion has at its radially inner end a radial annular flange formed with a cylindrical flange.
  • the invention also relates to a turbomachine equipped with an exhaust casing as described above.
  • the figure 1 represents a turbomachine exhaust casing 10 comprising two coaxial cylindrical walls, respectively radially internal 12 and external 14, connected by radial structural arms 16.
  • a cylindrical casing 18 is mounted around the radially inner wall 12 of the exhaust casing 10.
  • This envelope 18 shown separately on the figure 2 , comprises a cylindrical wall 20 in which are formed cutouts 22 open downstream for the passage of the radial arms 16 of the exhaust casing 10.
  • the cylindrical casing 18 comprises at its downstream end a radial annular flange 24 for attachment to the exhaust casing 10, and to its upstream end, a radial annular portion 26 extending radially inwardly.
  • the casing 18 comprises, according to the invention, an annular flange 28 formed at the radially inner end of its radial annular portion 26.
  • the casing 18 and the radially outer wall 14 of the exhaust casing delimit an annular space for exhaust gas flow inside a turbomachine, represented partially on the figure 3 .
  • This figure 3 shows the exhaust casing 10 mounted downstream of a low-pressure turbine 30, comprising discs 32 carrying blades 34, and rotating a shaft connected to an upstream compressor (not shown), in a manner well known.
  • the exhaust casing 10 comprises a downstream radial wall 36 extending radially outwardly from the downstream end of the inner wall 12 of the casing, and to which is fixed the radial annular flange 24 of the cylindrical casing.
  • the assembly formed by the inner wall 12 and the downstream radial wall 36 of the exhaust casing 10 as well as by the cylindrical casing 18 defines a toric cavity 38 commonly called a hub cavity.
  • the radial annular portion of the cylindrical envelope is free at its radially inner end and thus provides an annular opening in the hub cavity, between the free end of this radial annular portion and the upstream end of the inner wall of the exhaust casing.
  • the cylindrical casing 18 comprises an annular flange 28 formed at the inner end of the radial annular portion 26 of the casing, and engaged, as shown in FIG. figure 3 in an annular groove 40 ( Fig. 3a ) open towards the outside and formed by two radial flanges, respectively upstream 42 and downstream 44, arranged facing each other and integral with the inner wall 12 of the exhaust casing 10, to close the hub cavity 38 substantially sealingly and thus prevent the flow of fresh air into this cavity .
  • the downstream flange 44 is for example formed at the radially outer end of a ferrule 46 extending radially outwards from the upstream end of the inner wall 12 of the exhaust casing 10.
  • the upstream flange 42 can for its part be formed for example in the extension of a radial flange 48 for fixing an inner casing 50, commonly called an oil recovery casing, to the exhaust casing 10, the inner casing 50 extending axially between the shaft of the turbine and the discs 32 of the rotor of this turbine, upstream of the exhaust casing 10.
  • an inner casing 50 commonly called an oil recovery casing
  • annular flange 28 of the cylindrical casing 18 comprises at its radially outer end a cylindrical flange 52 extending upstream and forming a radial bearing abutment on the upstream annular flange 42 of the inner wall 12 of the exhaust casing 10.
  • the axial extent of the annular groove 40 is slightly greater than the thickness of the annular flange 28 of the cylindrical envelope 18 so that the latter is engaged with an axial clearance, for example of the order of 1 mm, in the groove 40, so as to allow radial sliding of the annular flange 28 in the groove 40.
  • cylindrical envelope 18 is formed such that at room temperature, when the turbomachine is stopped, the annular flange 18 extends substantially to the bottom of the annular groove 40.
  • the radial flanges 42 and 44 of the exhaust casing have radial dimensions greater than a value of radial displacement of the annular flange 28 considered as a maximum permissible under normal operating conditions of the turbomachine, in order to avoid any risk of disengagement of the engine. ledge 28 out of the throat 40.
  • cylindrical casing 18 is prestressed axially to apply, in stopping condition of the turbomachine, the upstream face 54 of the annular flange 28 against the downstream face 56 of the upstream flange 42 of the inner wall 12 of the casing. exhaust 10, to better ensure the sealing of the connection between the cylindrical casing 18 and the inner wall 12 of the housing.
  • the thermal expansion of the cylindrical envelope then tends to further increase the pressure exerted by the flange 28 on the upstream flange 42 of the casing, so that the sealing of the hub cavity 38 is ensured permanently.
  • the cylindrical envelope 18 could be prestressed axially to apply the downstream face 58 of the annular flange 28 against the upstream face 60 of the downstream flange 44 of the inner wall 12 of the exhaust casing 10.
  • the air pressure in the hub cavity 38 becomes greater than the air pressure upstream of the exhaust casing, or if a thermal expansion of the cylindrical casing 18 causes its annular flange 28 to move towards the upstream, it is quickly pressed against the upstream flange 42 of the exhaust casing, so that the sealing of the hub cavity 38 is preserved.
  • the cylindrical envelope 18 Because of the maintenance of its upstream end, the cylindrical envelope 18 has higher frequencies of frequencies of vibration than in the prior art.
  • the sealing of the hub cavity 38 makes it possible, as explained above, to improve the service life of the radial arms 16 of the exhaust casing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
EP08168877A 2007-12-14 2008-11-12 Dichtigkeit eines Nabenhohlraums eines Austrittsgehäuses in einem Turbotriebwerk Active EP2071142B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0708713A FR2925119A1 (fr) 2007-12-14 2007-12-14 Etancheite d'une cavite de moyeu d'un carter d'echappement dans une turbomachine

Publications (2)

Publication Number Publication Date
EP2071142A1 true EP2071142A1 (de) 2009-06-17
EP2071142B1 EP2071142B1 (de) 2010-06-23

Family

ID=39689098

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08168877A Active EP2071142B1 (de) 2007-12-14 2008-11-12 Dichtigkeit eines Nabenhohlraums eines Austrittsgehäuses in einem Turbotriebwerk

Country Status (7)

Country Link
US (1) US8172526B2 (de)
EP (1) EP2071142B1 (de)
JP (1) JP5320046B2 (de)
CA (1) CA2647058C (de)
DE (1) DE602008001592D1 (de)
FR (1) FR2925119A1 (de)
RU (1) RU2478801C2 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
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FR2956695A1 (fr) * 2010-02-25 2011-08-26 Turbomeca Support de palier arriere souple avec butee pour turbomachine
RU2578775C2 (ru) * 2010-07-26 2016-03-27 Снекма Система впрыска топлива для турбореактивного двигателя и способ сборки такой системы впрыска

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FR2923525B1 (fr) * 2007-11-13 2009-12-18 Snecma Etancheite d'un anneau de rotor dans un etage de turbine
US9062701B2 (en) * 2012-08-27 2015-06-23 United Technologies Corporation Pitch diameter shank bolt with shear sleeve
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
EP2938845A4 (de) 2012-12-29 2016-01-13 United Technologies Corp Turbinenabgasgehäusearchitektur
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
GB2524211B (en) 2012-12-29 2021-05-26 United Technologies Corp Turbine frame assembly and method of designing turbine frame assembly
US10378370B2 (en) 2012-12-29 2019-08-13 United Technologies Corporation Mechanical linkage for segmented heat shield
EP2938868B1 (de) 2012-12-29 2019-08-07 United Technologies Corporation Anordnung zur strömungsumlenkung
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
JP6271582B2 (ja) 2012-12-29 2018-01-31 ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ ガスタービンシールアセンブリおよびシール支持体
WO2014105780A1 (en) 2012-12-29 2014-07-03 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
WO2014105602A1 (en) 2012-12-29 2014-07-03 United Technologies Corporation Heat shield for a casing
US10240532B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Frame junction cooling holes
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
EP2938860B1 (de) 2012-12-31 2018-08-29 United Technologies Corporation Turbinenabgasgehäuse mit mehrteiligem rahmen
GB2524443B (en) 2012-12-31 2020-02-12 United Technologies Corp Turbine exhaust case multi-piece frame
JP6249499B2 (ja) 2012-12-31 2017-12-20 ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ タービン排気ケースのマルチピース型フレーム
US10330011B2 (en) * 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
FR3021692B1 (fr) * 2014-05-27 2016-05-13 Snecma Platine d'etancheite a fonction de fusible
JP2016003584A (ja) * 2014-06-13 2016-01-12 ヤンマー株式会社 ガスタービンエンジン
US11454128B2 (en) * 2018-08-06 2022-09-27 General Electric Company Fairing assembly
FR3099800B1 (fr) * 2019-08-09 2021-07-09 Safran Aircraft Engines Dispositif d'accrochage d'un boîtier d'alimentation en air d'un dispositif de refroidissement d'un carter de turbomachine
US11181004B2 (en) * 2020-02-07 2021-11-23 Raytheon Technologies Corporation Confinement of a rope seal about a passage using a backing plate

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JPH09324699A (ja) * 1996-06-05 1997-12-16 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンのフレーム構造
EP1262636A2 (de) * 2001-06-01 2002-12-04 General Electric Company Gasturbinenauslass zur Reduzierung der thermischen Spannungen und Methode zu dessen Herstellung
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JPH09324699A (ja) * 1996-06-05 1997-12-16 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンのフレーム構造
EP1262636A2 (de) * 2001-06-01 2002-12-04 General Electric Company Gasturbinenauslass zur Reduzierung der thermischen Spannungen und Methode zu dessen Herstellung
JP2003020957A (ja) 2001-07-11 2003-01-24 Ishikawajima Harima Heavy Ind Co Ltd タービンフレーム構造
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Cited By (5)

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Publication number Priority date Publication date Assignee Title
FR2956695A1 (fr) * 2010-02-25 2011-08-26 Turbomeca Support de palier arriere souple avec butee pour turbomachine
WO2011107694A1 (fr) * 2010-02-25 2011-09-09 Turbomeca Support de palier arriere souple avec butee pour turbomachine
RU2550417C2 (ru) * 2010-02-25 2015-05-10 Турбомека Гибкая опора заднего подшипника с упором для газотурбинного двигателя
US9194253B2 (en) 2010-02-25 2015-11-24 Turbomeca Flexible rear bearing mounting, having an abutment, for a turbine engine
RU2578775C2 (ru) * 2010-07-26 2016-03-27 Снекма Система впрыска топлива для турбореактивного двигателя и способ сборки такой системы впрыска

Also Published As

Publication number Publication date
CA2647058A1 (fr) 2009-06-14
JP2009144708A (ja) 2009-07-02
RU2008149138A (ru) 2010-06-20
US20090155071A1 (en) 2009-06-18
EP2071142B1 (de) 2010-06-23
US8172526B2 (en) 2012-05-08
FR2925119A1 (fr) 2009-06-19
JP5320046B2 (ja) 2013-10-23
CA2647058C (fr) 2015-02-17
DE602008001592D1 (de) 2010-08-05
RU2478801C2 (ru) 2013-04-10

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