EP4165286B1 - Ringförmige anordnung für eine turbomaschinenturbine - Google Patents

Ringförmige anordnung für eine turbomaschinenturbine Download PDF

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Publication number
EP4165286B1
EP4165286B1 EP21737109.5A EP21737109A EP4165286B1 EP 4165286 B1 EP4165286 B1 EP 4165286B1 EP 21737109 A EP21737109 A EP 21737109A EP 4165286 B1 EP4165286 B1 EP 4165286B1
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EP
European Patent Office
Prior art keywords
circumferentially
crown
annular
sealing means
annular assembly
Prior art date
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Application number
EP21737109.5A
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English (en)
French (fr)
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EP4165286A1 (de
Inventor
Rémi-Paul Honoré GODIER
Etienne Gérard Joseph CANELLE
Alexandre CORSAUT
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP4165286A1 publication Critical patent/EP4165286A1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the distributor 2 comprises an external annular platform 6 fixed to a radial blade 8.
  • the row of moving blades 4 comprises an external annular platform 10 from which extend radially outwards lips 12 cooperating in sealing with an abradabe 14, for example of the honeycomb type belonging to a sectored ring carried by the casing 16 as is illustrated in the figure 1 .
  • This sealing member provides better aerothermal sealing between the thermal deflector sectors.
  • the sealing member makes it possible to thermally protect the casing by preventing leaks of hot gases from combustion at the circumferential junctions of the thermal deflector sectors.
  • the first sealing means may comprise a wall element applied from downstream to the circumferentially facing ends of two circumferentially consecutive deflector sectors.
  • the design of the first sealing means in the form of a wall element eliminates doubts about the presence of the sealing member during an endoscopy inspection. This design also eliminates any risk of forgetting to install the sealing members but also the risk of making a mistake in the direction of assembly.
  • the shape of these bodies thus provides coding when they are mounted between two ring sectors.
  • Each sealing member may comprise a first junction element connecting a first plate to the wall element, this first junction element being inserted circumferentially between two edges of circumferentially adjacent deflector sectors.
  • first and second junction elements make it possible to mechanically maintain the first sealing means to the second sealing means.
  • the second junction element can be arranged radially outside two edges of circumferentially adjacent deflector sectors.
  • the present document relates to a turbine for a turbomachine comprising a low pressure turbine comprising an annular assembly according to the aforementioned characteristics and a high pressure turbine, the external casing of the low pressure turbine comprising an upstream annular flange for fixing to a downstream annular flange of a external casing of the high pressure turbine.
  • This document concerns a turbomachine comprising an annular assembly of the aforementioned type.
  • a turbine includes an upstream high pressure turbine and a downstream low pressure turbine.
  • the high pressure turbine and the low pressure turbine each comprise alternating annular rows of stator blades and moving blades arranged inside a casing.
  • a first downstream moving blade wheel 4 is surrounded externally by a casing of the low pressure turbine 16a while an upstream outlet distributor 2 of the high pressure turbine is surrounded externally by a casing of the high pressure turbine 16b.
  • the distributor 2 comprises an external annular platform 6 to which the radially external ends of radial blades 8 are connected.
  • a hooking tab 32 is at one end of said external platform 6 of the distributor 2. The circumferential and axial retention of the distributor 2 is ensured via said tab hook 32 which is engaged in an annular groove 33 of the high pressure turbine casing 16b, this annular groove 33 opening downstream.
  • This casing of the high pressure turbine 16b is fixed at its downstream end by means of an annular flange 36 to an annular flange 38 of the upstream end of the low pressure turbine casing 16a.
  • the annular flanges 36, 38 are positioned radially at the level of the annular space separating the outlet distributor 2 of the high pressure turbine and the first movable wheel 4 of the low pressure turbine.
  • the first moving blade wheel 4 is rotatably mounted around a longitudinal axis X in a ring attached to the external casing 16a of the low pressure turbine.
  • the sectorized ring is formed of several ring sectors which are arranged circumferentially end to end and each carried by the external casing 16a of the low pressure turbine. The downstream ends of the ring sectors are clamped radially by a C-shaped clamping tab 22, located downstream of the ring sectors.
  • the deflector sector 20 has a general z shape and has a substantially curved orientation.
  • the deflector sector 20 comprises, from upstream to downstream, a wall sector extending radially towards the inside 40, an annular wall sector 42 and a wall sector extending radially towards the outside 44.
  • the sector wall extending radially outwards 44 is fixed by brazing to a downstream edge of a radial wall 46 of the crown sector 18.
  • the annular wall sector 42 of the deflector sector 20 circumferentially follows the direction of extension of the sector of crown 18.
  • the abradable 14 is of the honeycomb type and provides sealing at the level of the blade wheel 4 by means of annular lips 12 extending radially outwards from the external annular platform 10 of the movable wheel 4 , in order to limit the passage of air radially outside the movable wheel 4.
  • sealing tabs 52 are inserted at the level of longitudinal slots located in the longitudinal edges of the circumferential ends of the annular wall sector 48 of the crown sector 18.
  • the radial edges of the circumferential ends of the radial wall sector 46 of the crown sector 18 and the longitudinal edges of the circumferential ends of the cylindrical wall sector 48 of the crown sector 18 comprise slots 54, 55 for housing a member of waterproofing.
  • the sealing member 56 comprises first circumferential sealing means 58 between two circumferentially consecutive sectors of deflector 20, that is to say at the junction between two circumferentially consecutive sectors of deflector 20. It can also include second sealing means 60 between two circumferentially consecutive crown sectors 18.
  • the first sealing means 58 comprise a wall element 62 comprising a downstream radial wall 64 extending radially outwards and whose radially internal end is connected to an inclined wall 66 converging towards the axis of rotation going towards upstream, this inclined wall 66 being connected at its upstream end to an upstream radial wall 68 extending radially inwards.
  • This wall element 62 is shaped identically to the sectors of thermal deflectors 20 so as to be able to perfectly match the three-dimensional shape of two edges of sectors of deflectors 20 facing each other circumferentially.
  • the second sealing means 60 between two circumferentially consecutive crown sectors 18 comprise a first plate 70 and a second plate 72 which are disjointed. These first 70 and second 72 plates have a planar, substantially rectangular shape.
  • the first plate 70 is able to be inserted on a first side into a slot 54 of an edge of a circumferential end of a cylindrical wall sector 50 of a first crown sector 18 and on a second side , opposite the first side, in a slot 54 of one edge of a circumferential end of a cylindrical wall sector 50 of a second circumferentially consecutive crown sector 18.
  • the second plate 72 is able to be inserted on a first side into a slot 55 of a radial edge of a circumferential end of a radial wall sector 46 of a first crown sector 18 and of a second side, opposite the first side, in a slot 55 of a radial edge of one end circumferential of a radial wall sector of a second circumferentially consecutive crown sector 18.
  • the sealing member 56 comprises a first junction element 74 connecting the first plate 70 to the inclined wall 66 converging towards the axis of rotation going upstream of the wall element 62.
  • the first junction element 74 extends radially with a substantially frustoconical shape with a section flaring radially inwards. This first junction element 74 is fixed at its radially internal end to the wall element 62 and its radially external end to the internal face of the first plate 70.
  • the first junction element 74 extends radially and longitudinally.
  • the sealing member 56 also comprises a second junction element 76 connecting the second plate 72 to the downstream radial wall 64 extending radially towards the outside of the wall element 62.
  • the second junction element extends longitudinally with a substantially rectangular shape.
  • This second junction element 76 is fixed at its radially internal end to the wall element 62 and its radially external end to the internal face of the second plate 72.
  • the second junction element 76 can extend radially up to a third of a radial length of the second plate 72 from an internal end of the second plate 72.
  • the first junction element 70 and the second junction element 72 are flat and have a thickness of between 0.2 and 0.4 mm. This thickness is of the same order of magnitude as that of the first and second sealing means.
  • This sealing member 56 can be manufactured by additive manufacturing. Said sealing member 56 is mounted in circumferential translation, the radially outer face of said wall element 62 coming to match the shape of the downstream face of the thermal deflector sector 20, the first 70 and second 72 plates being inserted into said slots 54, 55 housing two sectors of circumferentially consecutive crowns 18.
  • the sealing member 56 makes it possible to prevent combustion gases from passing through the circumferential and radial clearances present between two sectors of circumferentially consecutive crowns 18 and between two sectors of consecutive deflectors 20.
  • the sealing member 56 makes it possible to block the air in the gap between the first 70 and the second 72 disjointed plate.
  • the joining of the second sealing means 60 with the first sealing means 58 makes it possible to facilitate the assembly of said sealing member 56.
  • the circumferential sealing between two crown sectors 18 is thus carried out simultaneously with the sealing between two circumferentially consecutive deflector setters 20, which avoids assembly oversights.
  • the design of the first sealing means 58 in the form of a wall element 62 removes doubts about the presence of the sealing member 56 during an endoscopy inspection.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

  1. Ringförmige Anordnung für eine Turbine einer Turbomaschine, insbesondere eines Luftfahrzeugs, wobei sich die ringförmige Anordnung um eine Längsachse X erstreckt und umfasst:
    - einen Leitapparat (2), der an einem Außengehäuse (16) befestigt ist;
    - ein Schaufelrad (4), das stromabwärts des Leitapparats (2) angeordnet und drehbar im Inneren des Außengehäuses (16) gelagert ist;
    - wobei das Schaufelrad (4) von einem in Umfangsrichtung sektorisierten Ring umgeben ist, der von dem Außengehäuse (16) getragen wird und aus einem Kranz (18), der radial außerhalb des Schaufelrads (4) angeordnet ist, und einem ringförmigen Deflektor (20) gebildet ist, der von einer stromaufwärtigen Kante des Kranzes (18) getragen wird und sich von der stromaufwärtigen Kante des Kranzes (18) radial nach innen erstreckt;
    - Dichtungselemente (56) zwischen zwei in Umfangsrichtung aneinandergrenzenden Ringsektoren, wobei diese Dichtungselemente (56) in Umfangsrichtung verlaufende erste Dichtungseinrichtungen (58) umfassen, die an der Verbindungsstelle zwischen zwei in Umfangsrichtung aufeinanderfolgenden Deflektorsektoren (20) angeordnet sind,
    dadurch gekennzeichnet, dass
    die Dichtungselemente (56) in Umfangsrichtung verlaufende zweite Dichtungseinrichtungen (60) zwischen zwei in Umfangsrichtung aufeinanderfolgenden Kranzsektoren (18) umfassen, wobei diese zweiten Dichtungseinrichtungen (60) fest mit den ersten Dichtungseinrichtungen (58) verbunden sind.
  2. Ringförmige Anordnung nach Anspruch 1,
    wobei die ersten Dichtungseinrichtungen (58) ein Wandelement (62) umfassen, das von der stromabwärtigen Seite auf die in Umfangsrichtung einander gegenüberliegenden Enden von zwei in Umfangsrichtung aufeinanderfolgenden Deflektorsektoren (20) aufgebracht ist.
  3. Ringförmige Anordnung nach Anspruch 1 oder 2,
    wobei die zweiten Dichtungseinrichtungen (60) zumindest eine erste Platte (70) und eine zweite Platte (72) umfassen, die voneinander getrennt sind und beide mit den ersten Dichtungseinrichtungen (58) verbunden sind, wobei die erste Platte (70) und die zweite Platte (72) in einen Schlitz (54, 55) einer Kante eines ersten Kranzsektors (18) und mit einem anderen Abschnitt in einen Schlitz (54, 55) einer in Umfangsrichtung gegenüberliegenden Kante eines in Umfangsrichtung angrenzenden zweiten Kranzsektors (18) eingreifen.
  4. Ringförmige Anordnung nach Anspruch 3,
    wobei jedes Dichtungselement (56) ein erstes Verbindungsglied (74) umfasst, das eine erste Platte (70) mit dem Wandelement (62) verbindet, wobei dieses erste Verbindungsglied (74) in Umfangsrichtung zwischen zwei Kanten von in Umfangsrichtung aneinandergrenzenden Deflektorsektoren (20) angeordnet ist.
  5. Ringförmige Anordnung nach Anspruch 3 oder 4,
    wobei jedes Dichtungselement (56) ein zweites Verbindungsglied (76) umfasst, das eine zweite Platte (72) mit dem Wandelement (62) verbindet, wobei dieses zweite Verbindungsglied (76) in Umfangsrichtung zwischen zwei Kanten von in Umfangsrichtung aneinandergrenzenden Kranzsektoren (18) angeordnet ist.
  6. Ringförmige Anordnung nach Anspruch 5,
    wobei das zweite Verbindungsglied (76) radial außerhalb von zwei Kanten von in Umfangsrichtung aneinandergrenzenden Deflektorsektoren (20) angeordnet ist.
  7. Turbine für eine Turbomaschine mit einer Niederdruckturbine, die eine ringförmige Anordnung nach einem der vorhergehenden Ansprüche aufweist, und mit einer Hochdruckturbine, wobei das Außengehäuse der Niederdruckturbine einen stromaufwärtigen ringförmigen Flansch (36) zur Befestigung an einem stromabwärtigen ringförmigen Flansch (38) eines Außengehäuses der Hochdruckturbine aufweist.
  8. Turbomaschine mit einer ringförmigen Anordnung nach einem der Ansprüche 1 bis 6.
EP21737109.5A 2020-06-11 2021-06-10 Ringförmige anordnung für eine turbomaschinenturbine Active EP4165286B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2006131A FR3111382B1 (fr) 2020-06-11 2020-06-11 Ensemble annulaire pour turbine de turbomachine
PCT/FR2021/051043 WO2021250357A1 (fr) 2020-06-11 2021-06-10 Ensemble annulaire pour turbine de turbomachine

Publications (2)

Publication Number Publication Date
EP4165286A1 EP4165286A1 (de) 2023-04-19
EP4165286B1 true EP4165286B1 (de) 2024-05-22

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP21737109.5A Active EP4165286B1 (de) 2020-06-11 2021-06-10 Ringförmige anordnung für eine turbomaschinenturbine

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US (1) US12018576B2 (de)
EP (1) EP4165286B1 (de)
CN (1) CN115917120A (de)
FR (1) FR3111382B1 (de)
WO (1) WO2021250357A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3140112A1 (fr) * 2022-09-22 2024-03-29 Safran Aircraft Engines Amélioration de l’étanchéité dans une turbine de turbomachine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US7186078B2 (en) * 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
FR2899275A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
WO2014138320A1 (en) * 2013-03-08 2014-09-12 United Technologies Corporation Gas turbine engine component having variable width feather seal slot
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
FR3071273B1 (fr) * 2017-09-21 2019-08-30 Safran Aircraft Engines Ensemble d'etancheite de turbine pour turbomachine
FR3083563B1 (fr) 2018-07-03 2020-07-24 Safran Aircraft Engines Module d'etancheite de turbomachine d'aeronef

Also Published As

Publication number Publication date
FR3111382B1 (fr) 2022-12-23
EP4165286A1 (de) 2023-04-19
CN115917120A (zh) 2023-04-04
FR3111382A1 (fr) 2021-12-17
US12018576B2 (en) 2024-06-25
US20230340893A1 (en) 2023-10-26
WO2021250357A1 (fr) 2021-12-16

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