EP3390783A1 - Turbine ring assembly with support when cold and when hot - Google Patents
Turbine ring assembly with support when cold and when hotInfo
- Publication number
- EP3390783A1 EP3390783A1 EP16825493.6A EP16825493A EP3390783A1 EP 3390783 A1 EP3390783 A1 EP 3390783A1 EP 16825493 A EP16825493 A EP 16825493A EP 3390783 A1 EP3390783 A1 EP 3390783A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ring
- turbine
- flange
- sectors
- annular
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000463 material Substances 0.000 claims description 14
- 239000011153 ceramic matrix composite Substances 0.000 claims description 12
- 230000000284 resting effect Effects 0.000 claims 1
- 238000011144 upstream manufacturing Methods 0.000 description 10
- 238000012423 maintenance Methods 0.000 description 5
- 239000002184 metal Substances 0.000 description 5
- 229910052751 metal Inorganic materials 0.000 description 5
- 238000009941 weaving Methods 0.000 description 4
- 239000000919 ceramic Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 239000000835 fiber Substances 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 229920002134 Carboxymethyl cellulose Polymers 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 235000010948 carboxy methyl cellulose Nutrition 0.000 description 2
- 229920006184 cellulose methylcellulose Polymers 0.000 description 2
- 238000012710 chemistry, manufacturing and control Methods 0.000 description 2
- 229910000816 inconels 718 Inorganic materials 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 2
- 210000003462 vein Anatomy 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- YPIMMVOHCVOXKT-UHFFFAOYSA-N Multisatin Natural products O=C1C(C)C2C=CC(=O)C2(C)C(OC(=O)C(C)=CC)C2C(=C)C(=O)OC21 YPIMMVOHCVOXKT-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000000280 densification Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 239000003870 refractory metal Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910001247 waspaloy Inorganic materials 0.000 description 1
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.
- the invention provides, in a first aspect, a turbine ring assembly comprising a plurality of ceramic matrix composite ring sectors forming a turbine ring and a ring support structure having two annular flanges, each ring sector having an annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which extend at least two legs, the legs of each sector of ring being held between the two annular flanges of the ring support structure,
- each tab of the ring sectors has a portion projecting on its face facing one of the two annular flanges, this projecting portion cooperating with a housing present on the annular flange,
- each leg of the ring sectors comprises at least one opening in which is housed a portion of a holding member integral with the annular flange located opposite said tab, a clearance being present between the opening of said tab and the portion of the holding member in said opening, said holding member being of a material having a thermal expansion coefficient greater than the thermal expansion coefficient of the ceramic matrix composite material of the ring sectors.
- 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 may have at least one inclined portion forming, when observed in meridian section, a non-zero angle with respect to the radial direction and the axial direction and bearing on the portion protruding cooperating with said housing.
- 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 housing of the annular flange may have at least a first and a second inclined portions bearing on the projecting portion cooperating with said housing, said first and second inclined portions may each form, when observed in section meridian, a non-zero angle with respect to the radial direction and the axial direction.
- first inclined portion may bear against the radially inner half of the projecting portion and the second inclined portion may bear against 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) may be between (l + a C c) / (l + Qm) and l, lx (l + acMc) / (l + a m ) where a m denotes the coefficient of thermal expansion of said portion of the holding member and OCMC denotes the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, with m and O C MC being measured at 900 ° C and expressed in 10 " 6 ° C " 1 .
- each ring sector may have a Pi shape in axial section.
- the present invention also relates to a turbomachine comprising a turbine ring assembly as described above.
- FIG. 1 is a view in radial section of an exemplary turbine ring assembly according to the invention
- FIG. 2 is a detail of FIG. 1, and
- FIG. 3 and 4 schematically illustrate the mounting of a ring sector in the ring support structure of the ring assembly of Figure 1.
- FIG. 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 made of ceramic matrix composite material (CMC) and a metal ring support structure 3.
- the turbine ring 1 surrounds a set of blades 5.
- the turbine ring 1 is formed of a plurality of ring sectors 10, Figure 1 being a radial sectional view along a plane passing between two sectors of consecutive rings. Ring sectors 10 present in the example illustrated a Pi shape 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 inverted ⁇ -shaped section 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 direction 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.
- ai denotes the angle formed between the first inclined portion 360a and the radial direction DR
- a 2 denotes the angle formed between the first inclined portion 360a and the axial direction DA
- a 3 denotes the angle formed between the second inclined portion 360b and the radial direction DR
- a 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 metallic material, for example alloy AMI 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 di of the portion of the bands 40b present in the orifice 17 and the diameter d 2 of said orifice 17 is between (l + a C Mc) / (l + o m ) and l, lx (l + a C M C ) / (l + Om) where a m denotes the coefficient of thermal expansion of said portion of the frets 40b and a C Mc denotes the coefficient of thermal expansion of the This feature can also be verified for the ratio (diameter of the portion of the hoop 40a present in the orifice 15) / (diameter of the orifice 15).
- 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.
- 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 Figure 3 to increase the spacing between the flanges 32 and 36 and allow the insertion of the sector.
- ring 10 between the flanges 32 and 36 without risk of damaging the ring sector 10.
- the annular downstream radial flange 36 In order to facilitate the traction separation of the annular downstream radial flange 36, it comprises a plurality of hooks 39 distributed over its face 36b, face which is opposite the face 36a of the flange 36 opposite the downstream lugs 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 hooks 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
- 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 projecting portion 160 into the housing 360 and to align the orifices 17 and 37.
- the structure illustrated in FIG. 4 is then obtained in which the ring sectors 10 are kept cold by cooperation of projecting portions 140 and 160 and housing 320 and 360.
- a hoop 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 40b is engaged in the aligned orifices 37 and 17 formed respectively in the annular downstream radial flange 36 and in the downstream lug 16.
- the frets 40a and 40b are force-fitted into the annular flanges 32 and 36 to ensure their maintenance at 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.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1562741A FR3045715B1 (en) | 2015-12-18 | 2015-12-18 | TURBINE RING ASSEMBLY WITH COLD AND HOT HOLDING |
PCT/FR2016/053395 WO2017103451A1 (en) | 2015-12-18 | 2016-12-14 | Turbine ring assembly with support when cold and when hot |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3390783A1 true EP3390783A1 (en) | 2018-10-24 |
EP3390783B1 EP3390783B1 (en) | 2019-10-02 |
Family
ID=55411602
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16825493.6A Active EP3390783B1 (en) | 2015-12-18 | 2016-12-14 | Turbine shroud assembly and corresponding turbine |
Country Status (5)
Country | Link |
---|---|
US (1) | US10378386B2 (en) |
EP (1) | EP3390783B1 (en) |
CN (1) | CN108699918B (en) |
FR (1) | FR3045715B1 (en) |
WO (1) | WO2017103451A1 (en) |
Cited By (1)
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FR3093344A1 (en) * | 2019-03-01 | 2020-09-04 | Safran Ceramics | SET FOR A TURBOMACHINE TURBINE |
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FR3033825B1 (en) * | 2015-03-16 | 2018-09-07 | Safran Aircraft Engines | TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL |
FR3045716B1 (en) * | 2015-12-18 | 2018-01-26 | Safran Aircraft Engines | TURBINE RING ASSEMBLY WITH COLD ELASTIC SUPPORT |
FR3049003B1 (en) * | 2016-03-21 | 2018-04-06 | Safran Aircraft Engines | TURBINE RING ASSEMBLY WITHOUT COLD MOUNTING SET |
FR3056632B1 (en) | 2016-09-27 | 2020-06-05 | Safran Aircraft Engines | TURBINE RING ASSEMBLY INCLUDING A COOLING AIR DISTRIBUTION ELEMENT |
US11015613B2 (en) * | 2017-01-12 | 2021-05-25 | General Electric Company | Aero loading shroud sealing |
FR3087825B1 (en) * | 2018-10-29 | 2020-10-30 | Safran Aircraft Engines | TURBINE RING SECTOR WITH COOLED SEALING TABS |
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FR3090731B1 (en) * | 2018-12-19 | 2021-01-08 | Safran Aircraft Engines | Turbine ring assembly with curved rectilinear bearings. |
FR3095668B1 (en) * | 2019-05-03 | 2021-04-09 | Safran Aircraft Engines | Spacer-mounted turbine ring assembly |
FR3100838B1 (en) * | 2019-09-13 | 2021-10-01 | Safran Aircraft Engines | TURBOMACHINE SEALING RING |
US11215075B2 (en) | 2019-11-19 | 2022-01-04 | Rolls-Royce North American Technologies Inc. | Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring |
US11174795B2 (en) * | 2019-11-26 | 2021-11-16 | Raytheon Technologies Corporation | Seal assembly with secondary retention feature |
US11220930B2 (en) | 2019-12-03 | 2022-01-11 | Rolls-Royce Corporation | Assembly with pin-mounted ceramic matrix composite material components |
US11066947B2 (en) | 2019-12-18 | 2021-07-20 | Rolls-Royce Corporation | Turbine shroud assembly with sealed pin mounting arrangement |
FR3107549B1 (en) * | 2020-02-24 | 2022-09-16 | Safran Ceram | Sealing of a turbine |
US11215064B2 (en) * | 2020-03-13 | 2022-01-04 | Raytheon Technologies Corporation | Compact pin attachment for CMC components |
US11208911B2 (en) | 2020-04-23 | 2021-12-28 | Rolls-Royce Plc | Turbine shroud ring segments with ceramic matrix composite components |
US11215065B2 (en) | 2020-04-24 | 2022-01-04 | Rolls-Royce Corporation | Turbine shroud assembly with ceramic matrix composite components having stress-reduced pin attachment |
JP7256282B2 (en) * | 2020-05-11 | 2023-04-11 | 中国航発商用航空発動機有限責任公司 | Connection material and connection device for preventing thermal mismatch |
CN113638774B (en) * | 2020-05-11 | 2022-06-28 | 中国航发商用航空发动机有限责任公司 | Connecting piece and thermal mismatch prevention connecting device |
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US11220928B1 (en) | 2020-08-24 | 2022-01-11 | Rolls-Royce Corporation | Turbine shroud assembly with ceramic matrix composite components and cooling features |
US11208896B1 (en) | 2020-10-20 | 2021-12-28 | Rolls-Royce Corporation | Turbine shroud having ceramic matrix composite component mounted with cooled pin |
US11255210B1 (en) | 2020-10-28 | 2022-02-22 | Rolls-Royce Corporation | Ceramic matrix composite turbine shroud assembly with joined cover plate |
US11286812B1 (en) | 2021-05-25 | 2022-03-29 | Rolls-Royce Corporation | Turbine shroud assembly with axially biased pin and shroud segment |
US11629607B2 (en) | 2021-05-25 | 2023-04-18 | Rolls-Royce Corporation | Turbine shroud assembly with radially and axially biased ceramic matrix composite shroud segments |
US11346237B1 (en) | 2021-05-25 | 2022-05-31 | Rolls-Royce Corporation | Turbine shroud assembly with axially biased ceramic matrix composite shroud segment |
US11761351B2 (en) | 2021-05-25 | 2023-09-19 | Rolls-Royce Corporation | Turbine shroud assembly with radially located ceramic matrix composite shroud segments |
US11346251B1 (en) | 2021-05-25 | 2022-05-31 | Rolls-Royce Corporation | Turbine shroud assembly with radially biased ceramic matrix composite shroud segments |
US11959389B2 (en) * | 2021-06-11 | 2024-04-16 | Pratt & Whitney Canada Corp. | Turbine shroud segments with angular locating feature |
US11499444B1 (en) | 2021-06-18 | 2022-11-15 | Rolls-Royce Corporation | Turbine shroud assembly with forward and aft pin shroud attachment |
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 |
FR3142504A1 (en) * | 2022-11-24 | 2024-05-31 | Safran Ceramics | Turbine assembly for a turbomachine |
US12031443B2 (en) | 2022-11-29 | 2024-07-09 | Rolls-Royce Corporation | Ceramic matrix composite blade track segment with attachment flange cooling chambers |
US11773751B1 (en) | 2022-11-29 | 2023-10-03 | Rolls-Royce Corporation | Ceramic matrix composite blade track segment with pin-locating threaded insert |
US11713694B1 (en) | 2022-11-30 | 2023-08-01 | Rolls-Royce Corporation | Ceramic matrix composite blade track segment with two-piece carrier |
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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 |
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GB2245316B (en) * | 1990-06-21 | 1993-12-15 | Rolls Royce Plc | Improvements in shroud assemblies for turbine rotors |
FR2887601B1 (en) | 2005-06-24 | 2007-10-05 | Snecma Moteurs Sa | MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART |
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 (en) * | 2008-11-21 | 2014-06-27 | Turbomeca | POSITIONING DEVICE FOR RING SEGMENT |
WO2010103213A1 (en) | 2009-03-09 | 2010-09-16 | Snecma | Turbine ring assembly |
FR2954400B1 (en) * | 2009-12-18 | 2012-03-09 | Snecma | TURBINE STAGE IN A TURBOMACHINE |
JP2012211527A (en) * | 2011-03-30 | 2012-11-01 | Mitsubishi Heavy Ind Ltd | Gas turbine |
US11215081B2 (en) * | 2014-06-12 | 2022-01-04 | General Electric Company | Shroud hanger assembly |
FR3033826B1 (en) * | 2015-03-16 | 2018-11-23 | Safran Ceramics | TURBINE RING ASSEMBLY COMPRISING A PLURALITY OF RING SECTIONS IN CERAMIC MATRIX COMPOSITE MATERIAL |
FR3036435B1 (en) * | 2015-05-22 | 2020-01-24 | Safran Ceramics | TURBINE RING ASSEMBLY |
-
2015
- 2015-12-18 FR FR1562741A patent/FR3045715B1/en active Active
-
2016
- 2016-12-14 WO PCT/FR2016/053395 patent/WO2017103451A1/en active Application Filing
- 2016-12-14 EP EP16825493.6A patent/EP3390783B1/en active Active
- 2016-12-14 US US16/063,050 patent/US10378386B2/en active Active
- 2016-12-14 CN CN201680079488.9A patent/CN108699918B/en active Active
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3093344A1 (en) * | 2019-03-01 | 2020-09-04 | Safran Ceramics | SET FOR A TURBOMACHINE TURBINE |
WO2020178490A1 (en) * | 2019-03-01 | 2020-09-10 | Safran Ceramics | Assembly for a turbomachine turbine |
US11591924B2 (en) | 2019-03-01 | 2023-02-28 | Safran Ceramics | Assembly for a turbomachine turbine |
Also Published As
Publication number | Publication date |
---|---|
US10378386B2 (en) | 2019-08-13 |
US20180363507A1 (en) | 2018-12-20 |
WO2017103451A1 (en) | 2017-06-22 |
CN108699918A (en) | 2018-10-23 |
CN108699918B (en) | 2020-10-30 |
FR3045715A1 (en) | 2017-06-23 |
EP3390783B1 (en) | 2019-10-02 |
FR3045715B1 (en) | 2018-01-26 |
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