EP3390783B1 - Turbinendeckbandanordung und zugehörige turbine - Google Patents

Turbinendeckbandanordung und zugehörige turbine Download PDF

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Publication number
EP3390783B1
EP3390783B1 EP16825493.6A EP16825493A EP3390783B1 EP 3390783 B1 EP3390783 B1 EP 3390783B1 EP 16825493 A EP16825493 A EP 16825493A EP 3390783 B1 EP3390783 B1 EP 3390783B1
Authority
EP
European Patent Office
Prior art keywords
ring
turbine
sectors
cmc
annular
Prior art date
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Active
Application number
EP16825493.6A
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English (en)
French (fr)
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EP3390783A1 (de
Inventor
Clément ROUSSILLE
Thierry TESSON
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3390783A1 publication Critical patent/EP3390783A1/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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • 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
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • the field of application of the invention is in particular that of aeronautical gas turbine engines.
  • the invention is however applicable to other turbomachines, for example industrial turbines.
  • Ceramic matrix composite materials are known to retain their mechanical properties at high temperatures, which makes them suitable for constituting hot structural elements.
  • a set of metal turbine ring deforms under the effect of heat flow, which changes the clearance at the flow path and, therefore, the performance of the turbine.
  • ring segments in CMC significantly reduces the ventilation required to cool the turbine ring.
  • maintaining the ring sectors in position remains a problem in particular with respect to the differential expansions that can occur between the metal support structure and the CMC ring sectors.
  • another problem lies in controlling the shape of the vein both cold and hot without generating too much stress on the ring sectors.
  • the invention proposes, according to a first aspect, a turbine ring assembly according to claim 1.
  • the ring sectors are kept cold due to the cooperation between the protruding portions and the housings present on the annular flanges opposite them. Maintaining ring areas by this relief cooperation may no longer be ensured hot due to the expansion of the annular flanges.
  • the holding force is resumed by the expansion of the holding elements, which expansion does not entail significant stress on the ring sectors because of the presence of a cold clearance between the holding elements and the openings on the legs of the ring sector.
  • the housing of the annular flange has at least first and second inclined portions bearing on the projecting portion cooperating with said housing, said first and second inclined portions each forming, when observed in meridian section, a non-zero angle relative to in the radial direction and in the axial direction.
  • the radial direction corresponds to the direction along a radius of the turbine ring (straight connecting the center of the turbine ring to its periphery).
  • the axial direction corresponds to the direction along the axis of revolution of the turbine ring and the flow direction of the gas flow in the vein.
  • the first inclined portion may bear on the radially inner half of the projecting portion and the second inclined portion may be supported on the radially outer half of the projecting portion.
  • said at least one inclined portion may form an angle of between 30 ° and 60 ° with the radial direction.
  • the ratio (diameter of the part of the holding element present in said opening) / (diameter of said opening) can be between (1 + ⁇ CMC ) / (1 + ⁇ m ) and 1.1x (1 + ⁇ CMC ) / (1 + ⁇ m ) where ⁇ m denotes the coefficient of thermal expansion of said part of the holding element and ⁇ CMC denotes the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, ⁇ m and ⁇ CMC being measured at 900 ° C. and expressed as 10 -6 ° C -1 .
  • each ring sector may have a shape in Pi ( ⁇ ) in axial section.
  • the present invention also relates to a turbomachine comprising a turbine ring assembly as described above.
  • the figure 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 made of a ceramic matrix composite material (CMC) and a ring support metal structure 3.
  • the turbine ring 1 surrounds a set of rotary blades 5.
  • the turbine ring 1 is formed of a plurality of ring sectors 10, the figure 1 being a radial sectional view along a plane passing between two sectors of consecutive rings.
  • Ring sectors 10 present in the illustrated example a shape in Pi ( ⁇ ) in axial section.
  • the arrow DA indicates the axial direction with respect to the turbine ring 1 while the arrow DR indicates the radial direction with respect to the turbine ring 1.
  • Each ring sector 10 has a substantially P-shaped section ( ⁇ ) inverted with an annular base 12 whose inner face coated with a layer 13 of abradable material defines the flow stream of gas flow in the turbine.
  • Upstream and downstream tabs 14, 16 extend from the outer face of the annular base 12 in the radial direction DR.
  • upstream and downstream are used herein with reference to the flow direction of the gas flow in the turbine (arrow F).
  • the ring support structure 3 which is integral with a turbine casing 30 comprises an annular upstream radial flange 32 and an annular downstream radial flange 36.
  • the lugs 14 and 16 of each ring sector 10 are held between the flanges. 32 and 36.
  • Each of the annular flanges 32 and 36 defines a housing 320 and 360.
  • the housings 320 and 360 cooperate with a respective projecting portion 140 and 160 to ensure the cold maintenance of the ring sectors 10 on the structure ring support 3.
  • cold is meant in the present invention, the temperature at which the ring assembly is located when the turbine does not run, that is to say at room temperature which may be for example about 25 ° C.
  • each tab 14 and 16 comprises a portion of extra thickness forming the projecting portion 140 or 160.
  • the housings 320 and 360 each have, in the illustrated example, two inclined portions.
  • the housing 360 has a first inclined portion 360a and a second inclined portion 360b each forming a non-zero angle with the radial directions DR and axial DA.
  • the first and second inclined portions 360a and 360b bear on the projecting portion 160 cooperating with said housing 360.
  • the first 360a and second 360b inclined portions may not be parallel to each other, as illustrated.
  • the housing 360 may furthermore have a radial portion 360c extending along the radial direction DR and located between the first inclined portion 360a and the second inclined portion 360b.
  • the first 360a and second 360b inclined portions each form, when observed in meridian section, an angle of between 30 ° and 60 ° with the radial direction DR.
  • ⁇ 1 denotes the angle formed between the first inclined portion 360a and the radial direction DR
  • ⁇ 2 denotes the angle formed between the first inclined portion 360a and the axial direction DA
  • ⁇ 3 denotes the angle formed between the second portion inclined 360b and the radial direction DR
  • ⁇ 4 designates the angle formed between the second inclined portion 360b and the axial direction DA.
  • the first inclined portion 360a rests on the radially inner half Mi of the projecting portion 160 and the second inclined portion 360b bears against the radially outer half Me of the projecting portion 160.
  • the housing 320 located on the upstream flange 32 has a structure similar to that just described for housing 360.
  • each hoop 40a passes respectively through an orifice 35 formed in the radial flange.
  • annular upstream 32 and an orifice 15 formed in each upstream lug 14, the orifices 35 and 15 being aligned during the assembly of the ring sectors 10 on the ring support structure 3.
  • each hoop 40b passes respectively through an orifice 37 formed in the annular downstream radial flange 36 and a orifice 17 formed in each downstream tab 16, the orifices 37 and 17 being aligned during assembly of the ring sectors 10 on the ring support structure 3.
  • the locking frets 40a and 40b are made of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors 10.
  • the locking frets 40a and 40b may for example be made of metal material, for example alloy AM1 or Inconel 718.
  • a game J is present cold between the frets of block 40a, respectively 40b, and the orifices 15, 17 respectively, of the tabs 14, respectively 16.
  • the expansion of the locking bands 40a and 40b in the orifices 15 and 17 contributes to the hot maintenance of the ring sectors 10 on the structure ring support 3 reducing or even filling the clearance J.
  • the ratio between the diameter d 1 of the part of the frets 40b present in the orifice 17 and the diameter d 2 of said orifice 17 is between (1 + ⁇ CMC ) / (1 + ⁇ m ) and 1.1x (1 + ⁇ CMC ) / (1 + ⁇ m ) where ⁇ m denotes the coefficient of thermal expansion of said portion of the frets 40b and ⁇ CMC denotes the coefficient of thermal expansion of the material
  • inter-sector sealing is provided by sealing tabs housed in grooves facing in the opposite edges of two neighboring ring sectors.
  • a tongue 22a extends over almost the entire length of the annular base 12 in the middle portion thereof.
  • Another tab 22b extends along the tab 14 and on a portion of the annular base 12.
  • Another tab 22c extends along the tab 16. At one end, the tab 22c abuts the tab 22a and on the tongue 22b.
  • the tabs 22a, 22b, 22c are for example metallic and are mounted with cold clearance in their housings to ensure the sealing function at the temperatures encountered in operation.
  • Ventperes 33 formed in the flange 32 make it possible to bring cooling air to the outside of the turbine ring 1.
  • FIG. figure 1 The assembly of an exemplary turbine ring assembly as shown in FIG. figure 1 .
  • Each ring sector 10 described above is made of a ceramic matrix composite material (CMC) by forming a fibrous preform having a shape close to that of the ring sector and densifying the preform with a ceramic matrix.
  • CMC ceramic matrix composite material
  • the fiber preform it is possible to use ceramic fiber yarns, for example SiC fiber yarns, such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon", or carbon fiber yarns.
  • the fibrous preform is advantageously made by three-dimensional weaving, or multilayer weaving with the provision of debonding zones enabling the parts of preforms corresponding to the lugs 14 and 16 of the sectors 10 to be spaced apart.
  • the weaving may be of the interlock type, as illustrated.
  • the ring support structure 3 is made of a metallic material such as a Waspaloy® or Inconel 718 alloy.
  • the realization of the turbine ring assembly is continued by mounting the ring sectors 10 on the ring support structure 3.
  • the illustrated ring support structure 3 comprises at least one flange, here the flange radial downstream annular 36, which is elastically deformable in the axial direction DA of the ring.
  • the annular downstream radial flange 36 is pulled in the direction DA as shown in FIG. figure 3 in order to increase the spacing between the flanges 32 and 36 and to allow the insertion of the ring sector 10 between the flanges 32 and 36 without risk of damage to the ring sector 10.
  • the annular downstream radial flange 36 In order to facilitate pulling apart the annular downstream radial flange 36, it comprises a plurality of hooks 39 distributed on its face 36b, which face is opposite the face 36a of the flange 36 opposite the downstream tabs 16 of the ring sectors 10.
  • the traction in the axial direction DA exerted on the elastically deformable flange 36 is here carried out by means of a tool 50 comprising at least one arm 51 whose end comprises a hook 510 which is engaged in a hook 39 present on the outer face 36a of the flange 36.
  • the number of square brackets 39 distributed on the face 36a of the flange 36 is defined according to the number of tensile points that one wishes to have on the flange 36. This number depends mainly on the elastic nature of the flange.
  • Other forms and arrangements of means for exerting traction in the axial direction DA on one of the flanges of the ring support structure can of course be considered within the scope of the present invention.
  • the ring sector 10 is inserted between the annular flanges 32 and 36.
  • the projecting portion 140 is engaged in the housing 120 and the orifices 15 and 35 are aligned.
  • the flange 36 is then released in order to introduce the protruding portion 160 into the housing 360 and to align the orifices 17 and 37.
  • the structure illustrated in FIG. figure 4 in which the ring sectors 10 are kept cold by cooperation of the projecting portions 140 and 160 and the housings 320 and 360.
  • a band 40a is then engaged in the aligned orifices 35 and 15 respectively formed in the annular upstream radial flange 32 and in the upstream lug 14.
  • a hoop 40b is engaged in the aligned orifices 37 and 17 respectively formed in the annular downstream radial flange 36 and in the downstream lug 16.
  • the frets 40a and 40b are forced into the annular flanges 32 and 36 to ensure their maintenance cold (mounting H6P6 for example or other tight fixtures).
  • Each lug 14 or 16 of ring sector may comprise one or more orifices for the passage of one or more frets.
  • the ring sectors 10 are maintained by cooperation between the protruding portions 140 and 160 and the housings 320 and 360.
  • the expansion of the annular flanges 32 and 36 may no longer make it possible to maintain the sectors ring 10 at the housing 320 and 360.
  • the hot maintenance of the ring sectors 10 is then ensured by the expansion of the bands 40a and 40b in the orifices 15 and 17 which reduces or cancels the game J.

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

Claims (6)

  1. Turbinenringanordnung, umfassend eine Mehrzahl von Ringsektoren (10) aus einem Verbundwerkstoff mit keramischer Matrix, die einen Turbinenring (1) bilden, und eine Ringträgerstruktur (3) mit zwei Ringflanschen (32; 36), wobei jeder Ringsektor (10) einen ringförmigen Basisabschnitt (12) mit einer die Innenfläche des Turbinenrings definierenden Innenfläche und einer Außenfläche, von der sich mindestens zwei Schenkel (14; 16) erstrecken, aufweist, wobei die Schenkel (14; 16) jedes Ringsektors (10) zwischen den beiden Ringflanschen (32; 36) der Ringträgerstruktur (3) gehalten werden,
    wobei jeder Schenkel (14; 16) der Ringsektoren (10) einen vorstehenden Abschnitt (140; 160) auf seiner Fläche (14a; 16a) aufweist, die einem der beiden Ringflansche (32; 36) zugewandt ist, wobei der vorstehende Abschnitt (140; 160) mit einem auf dem Ringflansch (32; 36) vorhandenen Gehäuse (320; 360) zusammenwirkt,
    wobei jeder Schenkel (14; 16) der Ringsektoren (10) mindestens eine Öffnung (15; 17) aufweist, in der ein Teil eines Halteelements (40a; 40b) untergebracht ist, das mit dem ringförmigen Flansch (32; 36) fest verbunden ist, der gegenüber dem Schenkel (14; 16) angeordnet ist, wobei es ein Spiel (J) zwischen der Öffnung (15; 17) des Schenkels (14; 16) und dem Teil des Halteelements (40a; 40b) gibt, der sich in der Öffnung (15; 17) befindet, wobei das Halteelement (40a; 40b) aus einem Material besteht, das einen Wärmeausdehnungskoeffizienten aufweist, der größer ist als der Wärmeausdehnungskoeffizient des Verbundwerkstoffs mit keramischer Matrix der Ringsektoren (10),
    dadurch gekennzeichnet, dass das Gehäuse (320; 360) des ringförmigen Flansches (32; 36) mindestens einen ersten (360a) und einen zweiten (360b) geneigten Abschnitt aufweist, die an dem vorstehenden Abschnitt (140; 160) anliegen, der mit dem Gehäuse (320; 360) zusammenwirkt, wobei der erste (360a) und der zweite (360b) geneigte Abschnitt jeweils, wenn sie im Meridianschnitt betrachtet werden, einen Winkel ungleich Null (α1; α2; α3; α4) in Bezug auf die Radialrichtung (DR) und die Axialrichtung (DA) bilden.
  2. Anordnung nach Anspruch 1, wobei der erste geneigte Abschnitt (360a) an der radial inneren Hälfte (Mi) des vorstehenden Abschnitts (140; 160) anliegt und wobei der zweite geneigte Abschnitt (360b) an der radial äußeren Hälfte (Me) des vorstehenden Abschnitts (140; 160) anliegt.
  3. Anordnung nach Anspruch 1 oder 2, wobei mindestens einer der ersten und zweiten geneigten Abschnitte (360a; 360b) einen Winkel (α1; α3) zwischen 30° und 60° mit der Radialrichtung (DR) bildet.
  4. Anordnung nach einem der Ansprüche 1 bis 3, wobei das Verhältnis [Durchmesser (d1) des Teils des Halteelements (40a; 40b), der sich in der Öffnung (15; 17) befindet] / [Durchmesser (d2) dieser Öffnung (15; 17)] zwischen (1 + αCMC) / (1 + αm) und 1,1 x (1 + αCMC) / (1 + αm) beträgt, wobei αm den Wärmeausdehnungskoeffizienten des betreffenden Teils des Halteelements und αCMC den Wärmeausdehnungskoeffizienten des Verbundwerkstoffs mit keramischer Matrix der Ringsektoren bezeichnet, wobei αm und αCMC bei 900 °C gemessen und in 10-6.°C-1 ausgedrückt werden.
  5. Anordnung nach einem der Ansprüche 1 bis 4, wobei jeder Ringsektor (10) eine Pi-Form (π) im Axialschnitt aufweist.
  6. Turbomaschine, umfassend eine Turbinenringanordnung nach einem der Ansprüche 1 bis 5.
EP16825493.6A 2015-12-18 2016-12-14 Turbinendeckbandanordung und zugehörige turbine Active EP3390783B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1562741A FR3045715B1 (fr) 2015-12-18 2015-12-18 Ensemble d'anneau de turbine avec maintien a froid et a chaud
PCT/FR2016/053395 WO2017103451A1 (fr) 2015-12-18 2016-12-14 Ensemble d'anneau de turbine avec maintien a froid et a chaud

Publications (2)

Publication Number Publication Date
EP3390783A1 EP3390783A1 (de) 2018-10-24
EP3390783B1 true EP3390783B1 (de) 2019-10-02

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP16825493.6A Active EP3390783B1 (de) 2015-12-18 2016-12-14 Turbinendeckbandanordung und zugehörige turbine

Country Status (5)

Country Link
US (1) US10378386B2 (de)
EP (1) EP3390783B1 (de)
CN (1) CN108699918B (de)
FR (1) FR3045715B1 (de)
WO (1) WO2017103451A1 (de)

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US11441441B1 (en) 2021-06-18 2022-09-13 Rolls-Royce Corporation Turbine shroud with split pin mounted ceramic matrix composite blade track
US11319828B1 (en) 2021-06-18 2022-05-03 Rolls-Royce Corporation Turbine shroud assembly with separable pin attachment
US11499444B1 (en) 2021-06-18 2022-11-15 Rolls-Royce Corporation Turbine shroud assembly with forward and aft pin shroud attachment
FR3142504A1 (fr) * 2022-11-24 2024-05-31 Safran Ceramics Ensemble de turbine pour une turbomachine
US11773751B1 (en) 2022-11-29 2023-10-03 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating threaded insert
US11840936B1 (en) 2022-11-30 2023-12-12 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating shim kit
US11713694B1 (en) 2022-11-30 2023-08-01 Rolls-Royce Corporation Ceramic matrix composite blade track segment with two-piece carrier
US11732604B1 (en) 2022-12-01 2023-08-22 Rolls-Royce Corporation Ceramic matrix composite blade track segment with integrated cooling passages
US11885225B1 (en) 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016146942A1 (fr) * 2015-03-16 2016-09-22 Herakles Ensemble d'anneau de turbine comprenant une pluralité de secteurs d'anneau en matériau composite a matrice céramique.
WO2016189223A1 (fr) * 2015-05-22 2016-12-01 Herakles Ensemble d'anneau de turbine.

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2245316B (en) * 1990-06-21 1993-12-15 Rolls Royce Plc Improvements in shroud assemblies for turbine rotors
FR2887601B1 (fr) 2005-06-24 2007-10-05 Snecma Moteurs Sa Piece mecanique et procede de fabrication d'une telle piece
US7726936B2 (en) * 2006-07-25 2010-06-01 Siemens Energy, Inc. Turbine engine ring seal
US8070431B2 (en) * 2007-10-31 2011-12-06 General Electric Company Fully contained retention pin for a turbine nozzle
FR2938873B1 (fr) * 2008-11-21 2014-06-27 Turbomeca Organe de positionnement pour segment d'anneau
RU2522264C2 (ru) 2009-03-09 2014-07-10 Снекма Сборка обоймы турбины
FR2954400B1 (fr) * 2009-12-18 2012-03-09 Snecma Etage de turbine dans une turbomachine
JP2012211527A (ja) * 2011-03-30 2012-11-01 Mitsubishi Heavy Ind Ltd ガスタービン
CN106661952B (zh) * 2014-06-12 2019-09-03 通用电气公司 护罩吊架组件

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016146942A1 (fr) * 2015-03-16 2016-09-22 Herakles Ensemble d'anneau de turbine comprenant une pluralité de secteurs d'anneau en matériau composite a matrice céramique.
WO2016189223A1 (fr) * 2015-05-22 2016-12-01 Herakles Ensemble d'anneau de turbine.

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CN108699918B (zh) 2020-10-30
CN108699918A (zh) 2018-10-23
FR3045715B1 (fr) 2018-01-26
US10378386B2 (en) 2019-08-13
FR3045715A1 (fr) 2017-06-23
US20180363507A1 (en) 2018-12-20
WO2017103451A1 (fr) 2017-06-22
EP3390783A1 (de) 2018-10-24

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