EP3853445B1 - Turbinendichtung - Google Patents

Turbinendichtung Download PDF

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Publication number
EP3853445B1
EP3853445B1 EP19791320.5A EP19791320A EP3853445B1 EP 3853445 B1 EP3853445 B1 EP 3853445B1 EP 19791320 A EP19791320 A EP 19791320A EP 3853445 B1 EP3853445 B1 EP 3853445B1
Authority
EP
European Patent Office
Prior art keywords
annular
seal
radial
radially
walls
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
EP19791320.5A
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English (en)
French (fr)
Other versions
EP3853445A1 (de
Inventor
Frédéric Philippe Jean-Jacques PARDO
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 Helicopter Engines SAS
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Safran Helicopter Engines SAS
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Publication date
Application filed by Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Publication of EP3853445A1 publication Critical patent/EP3853445A1/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
    • 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
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb

Definitions

  • the present invention relates to the general field of devices ensuring a sealing function in a turbine stage in a turbomachine, such as a turbojet or an aircraft turboprop.
  • a turbine 10 comprises a plurality of stages 12 each formed of an annular row of fixed blades 14 carried externally by an external casing 16 and of an annular row of movable blades 18.
  • a radially external annular platform 20 is mounted at the radially outer end of the fixed vanes 14.
  • Each annular row of fixed vanes 14 forms a distributor 22.
  • the moving vanes 18 comprise a radially outer annular platform 24 comprising wipers 26 intended to cooperate with a ring 28 made of abradable material.
  • the terms radially inwards or radially outwards are to be understood in relation to a radial direction relative to the axis of rotation of the bladed wheel 18 which is the axis of rotation of the rotor of the turbine 10.
  • a first technical solution would consist of placing a seal between an external casing of the turbine and the platform radially external to the distributor.
  • the integration of the seal makes it possible to limit the flow rate of hot air leaking out of the vein.
  • the integration of the seal can cause heat conduction problems between the distributor and the external casing of the turbine. This thermal problem is due to the difficulty in achieving perfect contact between three distinct parts, namely the distributor, the seal and the external turbine casing. This optimal contact between the three parts makes it possible to limit hot air leaks but involves significant thermal conduction between the distributor and the external casing which mechanically weakens the latter.
  • the radially external platform 20 of the distributor 22 has an upstream end extending substantially longitudinally in the direction of the radially external platform 24 of the bladed wheel 18 provided with movable blades.
  • the downstream end of the radially external platform 20 has a radial flange 30 extending radially outwards.
  • the radially external platform 20 further comprises on its radially external face a shoulder 32.
  • An additional annular part 34 is fixed to the radially external platform 20 at the level of the shoulder 32.
  • the additional annular part 34 thus has a base 36.
  • the radially internal surface of the base 36 is in radial contact with the face radially external of the platform 20 and the longitudinally downstream surface of the base 36 is in longitudinal contact with the shoulder 32 of the radially external platform 20.
  • From a radially external end of the base 36 of the additional annular part 34 a first and a second annular wall 38, 40 extend.
  • first annular wall 38 extends from the radially outer upstream end of the base 36 and the second annular wall 40 extends from the radially outer downstream end of the base 36.
  • first and second annular walls 38, 40 respectively comprise a first part 38a, 40a and a second part 38b, 40b.
  • the first annular wall 38 comprises a first part 38a which extends along a radial component towards the outside and a longitudinal component towards the upstream and the second part 38b which extends only along a longitudinal component towards the upstream.
  • the second annular wall 40 comprises a first part 40a which extends along a radial component towards the outside and a longitudinal component towards the downstream and the second part 40b extends only along a longitudinal component towards the downstream.
  • the downstream end of the second annular wall 40 comes longitudinally close, without contact, or abuts on the radial flange 30 of the radially external platform 20 of the distributor 22.
  • the outer casing 16 has an annular groove 42 opening radially inwards, facing the distributor 22 and more precisely the additional annular part 34 fixed to the distributor 22.
  • An annular seal 44 is inserted into the annular groove 42 The seal 44 has an upstream end in contact with an upstream radial wall delimiting the annular groove 42 towards the upstream.
  • the annular seal 44 also has a downstream end in contact with a downstream wall delimiting the annular groove 42 towards the downstream.
  • the annular groove 42 of the external casing 16 also has a bottom. However, the seal 44 has no radial contact with the bottom of the annular groove 42.
  • a portion of the seal 44 inserted in the annular groove 42 projects radially inward with respect to the radially internal ends of the upstream and downstream walls delimiting the annular groove 42.
  • the radially internal end of the seal portion 44 projects from the annular groove 42 comes radially into abutment with the radially external surface of the second part 40b of the second annular wall 40 of the additional annular part 34, so as to form an annular surface contact.
  • part of the hot air flows out of the vein between the downstream end of the radially outer platform 24 of an upstream bladed blade wheel 18 and an upstream end of the radially outer platform of a distributor 22 arranged downstream of the bladed wheel 18.
  • the movement of this hot air outside the vein is limited by the presence of a baffle 46 formed using the first annular wall 38 of the additional annular part 34.
  • This baffle 46 makes it possible to divert part of the air intended to flow downstream of the first annular wall 38 of the additional annular part 34, in the part outside the vein.
  • the use of the additional annular part 34 makes it possible to limit the heat conduction from the distributor 22 to the external casing 16 of the turbine 10, so that the temperature of the external casing 16 is acceptable.
  • this additional annular part 34 is complex and the production of the latter is expensive. Furthermore, the integration of this annular part 34 does not make it possible to guarantee a good contact surface between the annular seal 44 and the second annular wall 40 of said annular part 34.
  • the invention aims to produce a sealing device making it possible to limit thermal conduction between the distributor 22 and the external casing 16 of the turbine while overcoming the problems mentioned above and this at a lower cost.
  • the present invention relates to an assembly for a staged turbine of a turbomachine, the assembly comprising a static sealing device, a turbine distributor comprising a radially external end and an external casing surrounding the distributor, the static sealing device being arranged radially between a radially outer end of the distributor and the outer casing, and comprising an annular seal carried by the distributor and an annular structure defining a plurality of radial annular walls spaced axially from each other, at least one first wall of said radial annular walls being in annular contact radially inwards with the annular seal, the longitudinal dimension of said at least one first wall being less than the longitudinal dimension of the seal.
  • At least one of the radial annular walls of the annular structure has a longitudinal dimension smaller than that of the seal, at the level of the contact zone between the seal and said radial annular wall, which makes it possible to reduce the contact surface between the seal and the annular structure. When this contact surface is reduced, it is easier to guarantee that the seal between the distributor and the external casing via the annular seal is ensured.
  • the contact surface is large, leak paths may appear between the annular seal and an annular structure of the external casing. These leaks can be caused by a lack of flatness of the surface in contact with the annular seal. The presence of leak paths impairs the seal between the distributor and the external casing of the turbine and reduces heat conduction between these parts.
  • the reduction of the contact surface makes it possible to improve the control and to limit the possibility of the existence of escape routes. The seal is thus improved if the contact surface between the seal and one of the radial walls of the annular structure is reduced.
  • the annular seal can be in annular linear contact with said at least one first radial annular wall of the annular structure.
  • the annular structure may have a hollow shape shaped so as to comprise at least two radial annular walls whose spacing in the longitudinal direction is less than the longitudinal dimension of the joint.
  • the fact that the spacing in the longitudinal direction of two adjacent radial annular walls of the annular structure is less than the longitudinal dimension of the joint makes it possible to guarantee that the annular joint is in contact, over the entire circumferentiality, with at least one of the radial annular walls of the annular structure.
  • the seal comes annularly into contact without discontinuity with the radially internal end of the radial wall annular of the annular structure.
  • the distributor may comprise a radial annular part comprising an annular groove opening radially outwards and receiving said annular seal.
  • the seal is housed in an annular groove which includes an upstream annular side and a downstream annular side.
  • the air flow in the turbine induces an overpressure on an upstream surface of the seal.
  • the seal is then compressed axially, at the level of its downstream surface, against the downstream annular flank of the annular groove. In this state of axial compression, the seal abuts on the downstream annular flank of the annular groove. In operation, the effects of pressure keep the seal resting on the downstream side of the groove.
  • the radially external end of the distributor in contact with the annular seal preferably has a groove opening radially outwards, more precisely opposite the annular structure, in order to receive the seal. This groove prevents any movement of the joint in a longitudinal direction. In this way, annular contact between the seal and the radially internal end of at least one radial annular wall is guaranteed.
  • the distributor comprises a radial annular part, in the thickness of which the groove is formed.
  • the annular seal may comprise at least two rings, and more particularly two rings, arranged longitudinally abutting one against the other.
  • the rings are split.
  • the slot in these split rings is sized to form a leak at the split portion of the ring as weakly as possible when the turbine is in operation.
  • Split rings exhibit radially inward elastic compression or radially outward elastic expansion depending on the desired cylindrical span. If a joint comprising two split rings is used, the rings are mounted angularly so that the slots are spaced from one another in order to avoid even partial overlapping of them which would allow an air leak hot.
  • the slots are positioned diametrically opposite each other.
  • each of the rings can be in annular contact with at least one radial annular wall of the annular structure.
  • the seal has at least two structurally independent rings arranged longitudinally in abutment allows each of these rings to be respectively in contact with at least one radially internal end of at least one radial annular wall.
  • the annular structure may have a plurality of cells opening radially towards the interior formed at least in part by the radial annular walls of the annular structure.
  • the static parts of a turbine have relative axial and radial movements between them.
  • the seal can move axially while guaranteeing radial contact with at least one of the radial annular walls of the annular structure.
  • the annular structure provided with radial annular walls forming cells is more abradable than conventional devices and the seal will adapt perfectly well to the opposite radial annular wall.
  • Each of the cells can have a hexagonal shape.
  • the cells could also have a triangular, square, rectangular or octagonal shape.
  • the longitudinal dimension of the joint is greater than or equal to half the longitudinal dimension of a cell.
  • the longitudinal dimension of the seal is greater than or equal to the dimension of a half cell, and more particularly less than the dimension of a cell
  • precise positioning of the groove receiving the seal and of the radial annular walls of the annular structure makes it possible to guarantee annular contact without discontinuity between the annular seal and the radially internal end of one of the radial annular walls.
  • the longitudinal dimension of the joint is greater than or equal to the longitudinal dimension of a cell.
  • the precise positioning of the groove receiving the seal and of the radial annular walls of the annular structure is not necessary to guarantee annular contact of the seal with at least one of the radial annular walls partially defining a plurality of cells.
  • the longitudinal dimension of the ring seal is greater than or equal to the longitudinal dimension of a cell, all of the lower ends of the walls defining the cell are in annular contact with the seal.
  • the longitudinal dimension of each of the rings of the seal is greater than or equal to half the longitudinal dimension of a cell.
  • the precise positioning of the groove receiving the seal and of the radial annular walls of the annular structure is necessary so that at least one of the two rings of the seal and at least one of the radial annular walls are in annular contact.
  • the longitudinal dimension of each of the rings of the seal is greater than or equal to the longitudinal dimension of a cell.
  • the precise positioning of the groove receiving the seal and of the radial annular walls of the annular structure is not necessarily necessary to guarantee annular contact between at least one of the two rings of the seal and the at least one radial annular walls of the annular structure.
  • the annular structure can be formed of several structurally independent sectors arranged circumferentially end to end.
  • the sectoring of the annular structure allows simple and easy assembly in a groove in the external casing opening radially towards the inside.
  • the annular contact between the annular seal or a ring, and the radially internal end of one of the radial annular walls is linear.
  • FIG. 2 illustrates a turbine comprising a sealing device according to the invention.
  • the distributor 22 has at its radially outer end a radially outer platform 20. From the radially outer platform 20, an annular projection 50 extends radially outwards.
  • the annular projection 50 has a connection zone 52 from which upstream and downstream radial annular walls 54, 56 extend in parallel radially outwards.
  • the upstream and downstream radial annular walls 54, 56 as well as the connection zone 52 of the projection 50 form an annular groove 58.
  • the upstream and downstream radial annular walls 54, 56 define sides of the annular groove while the connection zone 50 defines a bottom of the groove 58.
  • the annular groove 58 receives the annular seal 44.
  • the annular seal 44 is arranged in the groove so that a portion of the latter projects radially relative to the radially external ends of the upstream and downstream radial annular walls 54, 56 defining the groove 58.
  • the annular seal 44 has an upstream longitudinal surface abutting the upstream radial annular wall 54 of the groove 58 and a downstream longitudinal surface abutting the downstream radial annular wall 56 of the groove 58. These longitudinal stops of the seal 44 make it possible to maintain the annular seal 44 in position, without having to be radially in abutment with the bottom of the groove 58.
  • the external casing 16 has an annular groove 62 provided with a bottom 64 and two sides opening out radially.
  • the groove 62 opens radially inwards opposite the groove 58 of the distributor 22.
  • the groove 62 of the external casing 16 receives the annular structure 60 which is fixed to the bottom wall 64 of the groove 62 by the through an annular cylindrical 66.
  • the fixing of the annular structure 60 to the bottom wall 64 of the groove 62 formed on the external casing 16 can be carried out by brazing.
  • the annular structure 60 thus has an annular cylindrical wall 66, from which a plurality of radial annular walls 68 extend.
  • the radial annular walls 68 of the annular structure 60 are spaced longitudinally from each other.
  • the radial annular walls 68 of the annular structure 60 could be directly formed by laser fusion on the bottom wall 64 of the groove 62.
  • the radially outer end of the seal 44 is radially abutting with a radially inner end of at least one of the radial annular walls 68 of the annular structure 60.
  • the contact between the seal 44 and a radial annular wall 68 of the annular structure 60 is annular and without discontinuity.
  • the radial annular walls 68 have common wall sections 70.
  • the common wall sections 70 are spaced circumferentially from each other.
  • the radial annular walls 68 having common sections 58 form cells 72.
  • the annular structure 60 thus has a cellular structure 74 formed by the plurality of radial annular walls 68.
  • the plurality of cells 72 has a hexagonal structure.
  • the cells 72 could have a triangular, square, rectangular or octagonal shape.
  • FIG. 3B illustrates two longitudinally adjacent radial annular walls 68a, 68b of the annular structure 60 obtained by stamping a sheet. These longitudinally adjacent radial annular walls 68a, 68b have wall portions intended to be welded or brazed together at the level of the common sections 70.
  • the radial annular walls 68 of the annular structure 60 are obtained by additive manufacturing.
  • the annular seal 44 is arranged annularly in contact with the internal radial end of a radial annular wall 68.
  • the longitudinal dimension of the annular seal 44 must be sufficient to come into radial support at the upstream and downstream ends of the annular wall radial 68 with which it is in contact.
  • the spacing in a longitudinal direction between two longitudinally adjacent radial annular walls 68a, 68b is less than the longitudinal dimension of the annular seal 44. In this way, the annular seal 44 comes annularly into annular contact with the radially internal ends of the two longitudinally adjacent walls 68a, 68b.
  • the longitudinal dimension of the annular seal 44 must be at least equal to half the longitudinal dimension of a cell 72. In this way, by precise positioning of the radial annular walls 68 of the annular structure 60 and the groove 58 receiving the annular seal 44 makes it possible to guarantee annular contact of the seal with at least one of said radial annular walls 68.
  • the longitudinal dimension of the annular seal 44 is greater than the longitudinal dimension of a cell 72, then precise positioning of the radial annular walls 68 of the annular structure 60 and of the groove 58 receiving the annular seal 44 is not necessary to guarantee annular contact between the annular seal and at least one of the radially internal ends of the radial annular walls 68 of the annular structure 60.
  • annular seal 44 can then present an annular radial contact with the internal radial ends of two adjacent radial annular walls 68a, 68b.
  • the annular seal 44 has two rings 76a, 76b longitudinally abutting one against the other. These rings are preferably split.
  • the first ring 76a has an upstream end in longitudinal abutment with the upstream annular wall 54 of the annular groove 58 of the distributor 22 and a downstream end in longitudinal abutment with the upstream end of the second ring 76b.
  • the downstream end of the second ring 76b is in longitudinal abutment with the downstream radial annular wall 56 of the groove 58 of the distributor 22.
  • annular seal 44 When the annular seal 44 has two rings 76a, 76b arranged longitudinally in abutment, it is advantageous that each of them presents an annular radial contact with one of the radial annular walls 68 of the annular structure 60.
  • the radial annular walls 68a, 68c in contact with the rings 76a, 76b forming the annular seal 44 are not necessarily longitudinally adjacent, as is shown in Figure 4B .
  • a ring 76a, 76b can have a longitudinal dimension greater than the longitudinal spacing between two longitudinally adjacent radial annular walls 68a, 68b.
  • a ring 76a, 76b may have a longitudinal dimension greater than or equal to half the longitudinal dimension of a cell 72 or the longitudinal dimension of a cell 72.
  • the annular seal 44 or each ring 76a, 76b is annularly in contact with the radially internal end of a radial annular wall 68 of the annular structure 60.
  • the contact between the annular seal 44 or one of the rings 76a, 76b forming part of an annular seal 44 and a radial annular wall 68 is linear, so as to allow the reduction of the contact surface between the latter .
  • the reduction of the contact surface makes it possible to reduce the thermal conduction between the distributor 22 and the external casing 16 efficiently.
  • Said annular structure 60 is preferably composed of a plurality of structurally independent sectors arranged circumferentially in abutment. Such sectorization of the annular structure 60 makes it possible to arrange it in the annular groove 62 of the external casing 16 and to fix it to the latter.

Claims (11)

  1. Anordnung für eine gestufte Turbine (10) eines Turbotriebwerks, wobei die Anordnung eine statische Dichtungsvorrichtung, einen Turbinenleitapparat (22) mit einem radial äußeren Ende und ein den Leitapparat (22) umgebendes Außengehäuse (16) umfasst, wobei die statische Dichtungsvorrichtung radial zwischen einem radial äußeren Ende des Leitapparats (22) und dem Außengehäuse (16) angeordnet ist und eine von dem Leitapparat (22) getragene ringförmige Dichtung (44) und eine ringförmige Struktur (60) umfasst, die eine Vielzahl von axial voneinander beabstandeten radialen Ringwänden (68) definiert,
    dadurch gekennzeichnet, dass
    zumindest eine erste Wand der radialen Ringwände (68) radial nach innen in ringförmigem Kontakt mit der ringförmigen Dichtung (44) steht, wobei die Längsabmessung der zumindest einen ersten Wand kleiner ist als die Längsabmessung der Dichtung (44).
  2. Anordnung nach Anspruch 1,
    wobei die ringförmige Dichtung (44) in ringförmigem Linienkontakt mit der zumindest einen ersten radialen Ringwand (68) der ringförmigen Struktur (60) steht.
  3. Anordnung nach Anspruch 1 oder 2,
    wobei die ringförmige Struktur (60) eine Hohlform aufweist, die so ausgeformt ist, dass sie zumindest zwei radiale Ringwände (68) umfasst, deren Abstand in Längsrichtung kleiner ist als die Längsabmessung der Dichtung (44).
  4. Anordnung nach einem der vorhergehenden Ansprüche,
    wobei der Leitapparat (22) einen radialen ringförmigen Abschnitt mit einer ringförmigen Nut (58) aufweist, die radial nach außen mündet und die ringförmige Dichtung (44) aufnimmt.
  5. Anordnung nach einem der vorhergehenden Ansprüche,
    wobei die ringförmige Dichtung (44) zumindest zwei Ringe (76a, 76b) und insbesondere zwei Ringe (76a, 76b) umfasst, die in Längsrichtung aneinander anliegend angeordnet sind.
  6. Anordnung nach Anspruch 5,
    wobei jeder der Ringe (76a, 76b) in ringförmigem Linienkontakt mit zumindest einer radialen Ringwand (68) der ringförmigen Struktur (60) steht.
  7. Anordnung nach einem der vorhergehenden Ansprüche,
    wobei die ringförmige Struktur (60) eine Vielzahl von radial nach innen mündenden Zellen (72) aufweist, die zumindest teilweise aus den radialen Ringwänden (68) der ringförmigen Struktur (60) gebildet sind.
  8. Anordnung nach Anspruch 7,
    wobei jede der Zellen (72) eine hexagonale Form aufweist.
  9. Anordnung nach einem der Ansprüche 7 oder 8,
    wobei die Längsabmessung der Dichtung (44) größer oder gleich der halben Längsabmessung einer Zelle (72) ist.
  10. Anordnung nach einem der Ansprüche 7 bis 9,
    wobei die Längsabmessung der Dichtung (44) größer oder gleich der Längsabmessung einer Zelle (72) ist.
  11. Anordnung nach einem der vorhergehenden Ansprüche,
    wobei die ringförmige Struktur (60) aus mehreren strukturell unabhängigen Sektoren gebildet ist, die in Umfangsrichtung auf Stoß angeordnet sind.
EP19791320.5A 2018-09-20 2019-09-20 Turbinendichtung Active EP3853445B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1858527A FR3086324B1 (fr) 2018-09-20 2018-09-20 Etancheite d'une turbine
PCT/FR2019/052206 WO2020058648A1 (fr) 2018-09-20 2019-09-20 Etancheite d'une turbine

Publications (2)

Publication Number Publication Date
EP3853445A1 EP3853445A1 (de) 2021-07-28
EP3853445B1 true EP3853445B1 (de) 2024-04-17

Family

ID=64049423

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19791320.5A Active EP3853445B1 (de) 2018-09-20 2019-09-20 Turbinendichtung

Country Status (6)

Country Link
US (1) US11408298B2 (de)
EP (1) EP3853445B1 (de)
CN (1) CN112840105B (de)
CA (1) CA3113137A1 (de)
FR (1) FR3086324B1 (de)
WO (1) WO2020058648A1 (de)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6916154B2 (en) * 2003-04-29 2005-07-12 Pratt & Whitney Canada Corp. Diametrically energized piston ring
JP5045304B2 (ja) * 2007-08-16 2012-10-10 株式会社Ｉｈｉ ターボチャージャ
FR2949810B1 (fr) * 2009-09-04 2013-06-28 Turbomeca Dispositif de support d'un anneau de turbine, turbine avec un tel dispositif et turbomoteur avec une telle turbine
US8596969B2 (en) * 2010-12-22 2013-12-03 United Technologies Corporation Axial retention feature for gas turbine engine vanes
FR2989724B1 (fr) * 2012-04-20 2015-12-25 Snecma Etage de turbine pour une turbomachine
US9797515B2 (en) * 2012-09-28 2017-10-24 United Technologies Corporation Radially coacting ring seal
WO2017198916A1 (fr) * 2016-05-18 2017-11-23 Safran Aircraft Engines Procédé de fabrication d'une structure alvéolaire
ES2758187T3 (es) 2017-02-17 2020-05-04 MTU Aero Engines AG Disposición de sellado para una turbina de gas

Also Published As

Publication number Publication date
CA3113137A1 (fr) 2020-03-26
US11408298B2 (en) 2022-08-09
EP3853445A1 (de) 2021-07-28
US20210348518A1 (en) 2021-11-11
FR3086324B1 (fr) 2020-11-06
FR3086324A1 (fr) 2020-03-27
WO2020058648A1 (fr) 2020-03-26
CN112840105A (zh) 2021-05-25
CN112840105B (zh) 2023-06-09

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