EP2071142B1 - 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
EP2071142B1
EP2071142B1 EP08168877A EP08168877A EP2071142B1 EP 2071142 B1 EP2071142 B1 EP 2071142B1 EP 08168877 A EP08168877 A EP 08168877A EP 08168877 A EP08168877 A EP 08168877A EP 2071142 B1 EP2071142 B1 EP 2071142B1
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EP
European Patent Office
Prior art keywords
exhaust casing
wall
radial
cylindrical
annular
Prior art date
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Active
Application number
EP08168877A
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English (en)
French (fr)
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EP2071142A1 (de
Inventor
Xavier Firmin Camille Jean Lescure
Aurélien René-Pierre Massot
Sebastien Jean Laurent Prestel
Christian René Schnell
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP2071142A1 publication Critical patent/EP2071142A1/de
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    • 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 document JP 2003020957 describes a cylindrical envelope fixed at its downstream end on the inner wall of the exhaust casing and comprising at its upstream end an inwardly extending radial portion whose radially inner end is bolted to a flange of the casing; exhaust.
  • 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.

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  • 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)

Claims (10)

  1. Turbomaschinenaustrittsgehäuse (10) mit zwei koaxialen zylindrischen Wänden, radial innen (12) bzw. radial außen (24), die durch radiale Arme (16) verbunden sind, und einer zylindrischen Schale (18), die mit dem stromabwärts gelegenen Ende der radial inneren Wand (12) fest verbunden ist und einen Nabenhohlraum (38) mit der radial inneren Wand (12) sowie einen Abgassdömunigsraum mit der radial äußeren Wand (14) abgrenzt, wobei die zylindrische Schale (18) an ihrem stromaufwärts gelegenen Ende einen ringförmigen radialen Teil (26) aufweist, der sich ins Innere der Turbomaschine erstreckt, dadurch gekennzeichnet, dass der ringförmige radiale Teil (26) an seinem inneren Ende einen ringförmigen Rand (28) aufweist, der durch radiales Gleiten im Wesentlichen auf Dichtigkeit mit der inneren zylindrischen Wand (12) des Austrittsgehäuses (10) zusammenwirkt.
  2. Austrittsgehäuse (10) nach Anspruch 1, dadurch gekennzeichnet, dass die innere Wand (12) des Austrittsgchäuses (10) zwei ringförmige Flansche, stromaufwärts (42) bzw. stromabwärts (44) gelegen, aufweist, die sich radial nach außen erstrecken und derart gegenüber einander angeordnet sind, dass sie eine ringförmige Einschnürung (40) bilden, die dazu bestimmt ist, den ringförmigen Rand (28) der zylindrischen Schale (18) mit einem axialen Spiel für eine dichte Verbindung der zylindrischen Schale (18) mit der radial inneren Wand (12) aufzunehmen, die eine radiale Verschiebung des ringförmigen Randes (28) der Schale (18) zulässt.
  3. Austrittsgehäuse (10) nach Anspruch 2, dadurch gekennzeichnet, dass die beiden Flansche (42, 44) der inneren Wand (12) des Austrittsgehäuses (10) eine radiale Abmessung haben, die höher als eine maximal zulässige Amplitude einer radialen Verschiebung des ringförmigen Randes (28) der zylindrischen Schale (18) ist, die durch deren Wärmeausdehnung hervorgerufen wird.
  4. Austrittsgehäuse (10) nach Anspruch 2 oder 3, dadurch gekennzeichnet, dass sich der ringförmige Rand (28) der zylindrischen Schale (18) im Wesentlichen bis zum Boden der ringförmigen Einschnürung (40) der inneren Wand (12) des Austrittsgehäuses (10) im Haltezustand der Turbomaschine erstreckt.
  5. Austrittsgehäuse (10) nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, dass die zylindrische Schale (18) im Haltezustand der Turbomaschine derart vorgespannt ist, dass sie die stromaufwärts gelegene Seite (54) des ringförmigen Randes (28) ihres radialen ringförmigen Teils (26) gegen den stromaufwärts gelegenen ringförmigen Flansch (42) der inneren Wand (12) des Austrittsgehäuses drückt, um die Dichtigkeit des Nabenhohlraums (38) zu gewährleisten.
  6. Austrittsgehäuse (10) nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, dass die zylindrische Schale (18) im Haltezustand der Turbomaschine derart vorgespannt ist, dass sie die stromabwärts gelegene Seite (58) des ringförmigen Randes (28) ihres radialen ringförmigen Teils (26) gegen den stromabwärts gelegenen ringförmigen Flansch (44) der inneren Wand (12) des Austrittsgeliäuses rückt, um die Dichtigkeit des Nabenhohlraums (38) zu gewährleisten.
  7. Austrittsgehäuse (10) nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der ringförmigen Rand (28) des radialen ringförmigen Teils (26) der zylindrischen Schale (18) an seinem radial äußeren Ende einen zylindrischen Kragen (52) aufweist, der sich nach stromaufwärts erstreckt und einen radialen Anlageanschlag an dem ringförmigen, stromaufwärts gelegenen Flansch (42) der inneren Wand (12) des Austrittsgehäuses (10) bildet.
  8. Austrittsgehäuse (10) nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass der radiale innere Teil (26) der zylindrischen Schale (18) Öffnungen aufweist, die zum Durchgang eines Entlüfumgsluftstroms bestimmt sind.
  9. Zylindrische Schale (18) für ein Turbomaschmenaustrittsgehäuse (10) nach einem der vorhergehenden Ansprüche, welche an einem ihrer Enden einen ringförmigen Flansch (24) und am anderen ihrer Enden einen radialen ringförmigen Teil (26) aufweist, der sich nach innen erstreckt, dadurch gekennzeichnet, dass der radiale ringförmige Teil (26) an seinem radial inneren Ende einen radialen ringförmigen Rand (28) aufweist, der mit einem zylindrischen Kragen ausgebildet und dazu bestimmt ist, durch radiales Gleiten im Wesentlichen auf Dichtigkeit mit einer zylindrischen Wand des Austrittsgehäuses zusammenwirkt.
  10. Turbomaschine, dadurch gekennzeichnet, dass sie ein Austrittsgehäuse (10) nach einem der Ansprüche 1 bis 8 aufweist.
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

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

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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)

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US20090155071A1 (en) 2009-06-18
CA2647058C (fr) 2015-02-17
JP2009144708A (ja) 2009-07-02
FR2925119A1 (fr) 2009-06-19
EP2071142A1 (de) 2009-06-17
CA2647058A1 (fr) 2009-06-14
JP5320046B2 (ja) 2013-10-23
US8172526B2 (en) 2012-05-08
DE602008001592D1 (de) 2010-08-05
RU2008149138A (ru) 2010-06-20
RU2478801C2 (ru) 2013-04-10

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