US3864056A - Cooled turbine blade ring assembly - Google Patents

Cooled turbine blade ring assembly Download PDF

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Publication number
US3864056A
US3864056A US383426A US38342673A US3864056A US 3864056 A US3864056 A US 3864056A US 383426 A US383426 A US 383426A US 38342673 A US38342673 A US 38342673A US 3864056 A US3864056 A US 3864056A
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US
United States
Prior art keywords
ring
ring segments
heat shield
disposed
segments
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.)
Expired - Lifetime
Application number
US383426A
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English (en)
Inventor
Frank K Gabriel
Stephen D Leshnoff
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.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Priority to US383426A priority Critical patent/US3864056A/en
Priority to CA203,410A priority patent/CA995140A/en
Priority to IT24694/74A priority patent/IT1015601B/it
Priority to DE2432092A priority patent/DE2432092A1/de
Priority to NL7409533A priority patent/NL7409533A/xx
Priority to GB3156974A priority patent/GB1463344A/en
Priority to CH1021374A priority patent/CH583849A5/xx
Priority to FR7426138A priority patent/FR2238838B1/fr
Priority to JP8527874A priority patent/JPS5322601B2/ja
Priority to SE7409739A priority patent/SE385493B/xx
Application granted granted Critical
Publication of US3864056A publication Critical patent/US3864056A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D11/08—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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • a cooling air chamber directs cooling fluid to [22] Fil d; J l 27 1973 each stator vane retainer arrangement and to each ring segment which is circumferentially disposed [21] Appl' 383,426 about each rotor disc.
  • the ring segments have a heat shield disposed on their outward side.
  • the stator vane [52] us. c1 415/178, 415/177, 415/116 retainer arrangement including the ring Segments and [51] I Cl Fo 25/0 o 25/14 o 25/12 heat shields are maintained in a controlled tempera- [5 Fi ld f Search 415 15 116, 7 3 ture and in a controlled pressurized state.
  • a bias pro- 415 137 17 177 ducing means holds the heat shield and ring segments in a radially inwardly directed position, against the [56] References Cited blade ring, to which it transfers reaction loads.
  • the UNITED STATES PATENTS flow of cooling fluid maintains the heat shield and ring 2427 244 9 9 w segments at a controlled temperature, while it pre- 3034298 x 2; ig?
  • This invention relates generally to gas urb es. an structure shown therein comprises an axial flow gas turmore particularly, to cooled blade ring assemblies disposed about the blades of the gas turbine.
  • a plurality of blade ring segments and vane shroudings are disposed circumferentially about the turbine axis and rotor.
  • the blade ring segments and stationary flow path segments define an annular cooling fluid flow chamber, from which cooling fluid is channeled through passageways into each stator vaneassembly.
  • cooling fluid is passed under pressure through passageways from the annular chamber to impinge upon a heat radiation shield which is attached to each of a plurality of circumferential disposed ring segments.
  • the heat shield cooperates with a spring member that maintains the radiation shield and its attached ring in a generally stationary yet expendable position.
  • the cooling fluid passes around the shield creating a pressure differential between the cooling air chamber and the hot motive fluid gaseous flow path, preventing the hot working gaseous fluid from entering and damaging the cooling air chamber and its contiguous blade ring structure.
  • FIG. 1 is a diagrammatic view of a gas turbine engine embodying this invention, with parts broken away;
  • FIG. 2 is an enlarged view of the cooled blade ring assembly of FIG. 1;
  • FIG. 3 is one embodiment of a ring segment cooling arrangement
  • FIG. 4 is a perspective view of the radiation shield.
  • a nozzle or row one array of stationary vanes 24 is disposed upstream of the first array of the rotating blades I8. Between the first two arrays of rotating blades 18 and 20 there is disposed another circumferential array of stationary blades 26. Downstream of the second array of rotating blades 20 there is disposed another array of circumferentially disposed stationary vanes 28, followed by another array of rotating blades 22.
  • a combuster 30 supplies the hot motive fluid which passes through the nozzle 24 and into the blades 18, 20 and 22, thereby causing their respective rotors 12, 14 and 16 to rotate.
  • the hot motive fluid travels through an annular flow path, defined on its radially inward portion by a plurality of shroud rings 32 supporting the radially inner portion of the stationary vanes 24, 26 and 28 and by a plurality of blade platforms 34.
  • a blade platform 34 is provided on each radially inward portion of each air foil 23.
  • the hot motive fluid flow path is defined on its radially outward portion by a plurality of circumferentially disposed outer vane segments 35, a blade ring 36, and a plurality of ring segments 37.
  • the entire turbine 10 is enclosed in a turbine cylinder 38', only a portion of which is shown in FIG. 1.
  • High efficiency and high power output of the turbine requires cooling of the surfaces of the boundaries defining the hot motive fluid flow path. Without cooling of these surfaces, the entire turbine structure would have to be constructed of a more exotic, more expensive material, if such materials are even available, that would withstand the high thermal effects of the more powerful turbine.
  • Cooling is performed in this invention, by providing a cooling inlet 40 disposed through the turbine cylinder 38. Pressurized cooling fluid is supplied to the inlet 40 from a source, not shown. This cooling fluid is received in an annular chamber 42 defined by the blade ring 36. The annular chamber 42, for receiving the cooling fluid, is shown more clearly in FIG. 2.
  • a ring segment cooling arrangement 44 is shown more clearly in FIGS. 2 and 3.
  • the ring segment cooling arrangement 44 is shown disposed circumferentially about the hot motive fluid flow path, radially outwardly of the rotating arrays of the blades 18 and 20.
  • the ring segment cooling arrangement 44 includes the ring segments 37, which are positioned in an annular array around and adjacent the hot motive fluid flow path.
  • a heat shield 46 shown in FIG. 4, is attached to the radially outer side of each ring segment 37.
  • the shield 46 comprises a corrugated member 48 welded to the radially inward side of a sheet member 50. Only a central linear segment of the shield 46 is welded to the ring segment 37 This allows for expansion due to thermal effects for the individual portions of the heat shield 46.
  • the corrugated member 48 prevents much of the heat transfer from the hot fluid flow path to the blade ring 36, and therefore, acts as an insulator.
  • the heat shield 46 is cooled by an impingement of cooling fluid ejected from a plurality of holes or jets 51 disposed in the radially inner end of a radially directed chamber 52.
  • the chamber 52 acts as a cooling fluid conduit.
  • the chamber 52 is held in a compressive state against the shield 46 by a spring 54.
  • the spring 54 and chamber 52v cooperate with and are disposed within a sleeve-like tube 56 that is attached to the blade ring 36.
  • Theradially outer end of tube 56 is disposed within the cooling fluid chamber 42 of the blade ring 36.
  • the cooling fluid is forced in a cooling fluid inlet orifice 57 on the outer end of tube 56.
  • the cooling fluid passes through the spring member 54, and into the chamber 52.
  • the fluid is then forced out the openings 51 in the' radially inner end of chamber 52.
  • the fluid impinges upon and flows over the shield 46.
  • the spent cooling fluid escapes around the axially disposed portion of the ring segments 37 through a plurality of gaps 58 which are disposed circumferentially around the ring segments 37 between the ring segments 37 and the supporting adjacent vane segments 35, and/or the fluid escapes through an annular array of passageways 65 disposed in shoulder portion 35A, as shown in FIG. 3.
  • cooling fluid passes into the hot motive fluid flow path, it creates a pressure differential between the motive fluid flow path and the coolant fluid flow passageways. This differential in pressure prevents any hot motive fluid from entering the ring segment cooling arrangement 44 or the blade ring structure 36.
  • the spring member 54 holding the chamber 52 and the shield 46 in a compressed state of engagement with the vane segments 35 allows for thermal growth in a radial direction of each of the ring segments 37 and their respective shield members 46. Axial changes due to thermal expansion are permitted because of'an overlap arrangement between the axially disposed, circumferentially directed lip portions 37A of the ring segments 37 and the axially disposed circumferentially directed shoulder portions 35A of the adjacent vane supporting segments 35.
  • the vane supporting segments 35 themselves are cooled by the flow of pressurized cooling fluid entering a plurality of circumferentially disposed orifices 59 in the blade ring 36 as shown in FIG. 2.
  • the orifices 59 supply the cooling fluid from the cooling fluid chamber 42 within the blade ring 36 and permit the cooling fluid to pass through the first array of stationary vanes 24.
  • the coolant fluid entering the annular arrays of downstream orifices 59' provide cooling for the stationary vanes 26 and 28, as shown in FIG. 2.
  • the fluid impinges upon a splash shield 60 that directs the cooling fluid to flow near the axially disposed portions of each of the vane segments 35.
  • the axially disposed portions of the stationary vane segments 35 are near those members that provide support for the ring segments 37.
  • This cooling effect minimizes thermal growth of the vane segments, the blade rings and the supporting structure, and permits the manufacture of a high performance turbine with a satisfactory metal creep life from a more common, less heat resistant and less expensive metal.
  • the ring segments could be compressed by a different arrangement of bias producing members.
  • the cooling fluid could be ejected from several tubes extending from the cooling air chamber; and the heat shield is susceptible to various modifications.
  • a hot elastic fluid machine comprising: a turbine casing, a plurality of rotatable discs mounted on an axis, a plurality of rotor blades disposed on the periphery of each of said rotatable discs, a plurality of radially directed stationary blades disposed in annular arrays alternating with said rotatable discs.
  • each annular array of stationary blades having an inner and an outer shroud ring, a blade ring circumferentially disposed about the blades, means for supplying said stationary blades with cooling fluid, a plurality of insulated ring segments coaxial with said blade ring disposed radially outwardly of said rotating blades and inwardly of said blade ring, conduit means for supplying pressurized cooling fluid to said ring segments, said ring segments disposed about said rotating blades being expansible in both the radial and the axial direction, said radial direction of expansion of said.
  • ring segments being controlled by a biasing means, and a heat shield, said heat shield being disposed in a spaced relationship and radially outwardly of, yet fixedly attached to, said ring segments, said heat shield being cooled by chambers having a passageway extending therethrough, said passageway permitting the flow of cooling fluid through said bias producing means, the radially innermost chamber having holes therein, said holes permitting the pressurized cooling fluid to impinge upon said heat shield, the flow of cooling fluid upon said heat shield preventing localized overcooling and hence preventing localized distortion of said ring segments thereby, said heat shield receiving heat from said ring segments by radiation and convection to permit a uniform temperature across said ring segments and, said heat shield providing a heat barrier between said blade ring and said ring segments.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US383426A 1973-07-27 1973-07-27 Cooled turbine blade ring assembly Expired - Lifetime US3864056A (en)

Priority Applications (10)

Application Number Priority Date Filing Date Title
US383426A US3864056A (en) 1973-07-27 1973-07-27 Cooled turbine blade ring assembly
CA203,410A CA995140A (en) 1973-07-27 1974-06-25 Cooled turbine blade ring assembly
IT24694/74A IT1015601B (it) 1973-07-27 1974-07-02 Anelli porta palette raffreddati
DE2432092A DE2432092A1 (de) 1973-07-27 1974-07-04 Turbine mit heissem, elastischem treibmittel
NL7409533A NL7409533A (nl) 1973-07-27 1974-07-15 Gekoelde turbineschoepringconstructie.
GB3156974A GB1463344A (en) 1973-07-27 1974-07-17 Gas turbine
CH1021374A CH583849A5 (xx) 1973-07-27 1974-07-24
FR7426138A FR2238838B1 (xx) 1973-07-27 1974-07-26
JP8527874A JPS5322601B2 (xx) 1973-07-27 1974-07-26
SE7409739A SE385493B (sv) 1973-07-27 1974-07-26 Kyld turbinskovelring

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US383426A US3864056A (en) 1973-07-27 1973-07-27 Cooled turbine blade ring assembly

Publications (1)

Publication Number Publication Date
US3864056A true US3864056A (en) 1975-02-04

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Family Applications (1)

Application Number Title Priority Date Filing Date
US383426A Expired - Lifetime US3864056A (en) 1973-07-27 1973-07-27 Cooled turbine blade ring assembly

Country Status (10)

Country Link
US (1) US3864056A (xx)
JP (1) JPS5322601B2 (xx)
CA (1) CA995140A (xx)
CH (1) CH583849A5 (xx)
DE (1) DE2432092A1 (xx)
FR (1) FR2238838B1 (xx)
GB (1) GB1463344A (xx)
IT (1) IT1015601B (xx)
NL (1) NL7409533A (xx)
SE (1) SE385493B (xx)

Cited By (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USB563412I5 (xx) * 1975-03-28 1976-02-24
US4019320A (en) * 1975-12-05 1977-04-26 United Technologies Corporation External gas turbine engine cooling for clearance control
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
FR2428141A1 (fr) * 1978-06-05 1980-01-04 Gen Electric Dispositif perfectionne de support de virole de turbine
FR2450344A1 (fr) * 1979-02-28 1980-09-26 Mtu Muenchen Gmbh Dispositif pour reduire au minimum et maintenir constants les jeux a la crete des aubes existants dans les turbines axiales, notamment pour turbomachines a gaz
FR2450345A1 (fr) * 1979-02-28 1980-09-26 Mtu Muenchen Gmbh Dispositif pour reduire au minimum et maintenir constants des jeux existant dans les turbines axiales, notamment turbomachines a gaz
US4317646A (en) * 1979-04-26 1982-03-02 Rolls-Royce Limited Gas turbine engines
FR2509373A1 (fr) * 1981-07-11 1983-01-14 Rolls Royce Couronne enveloppante reglable pour aubes mobiles de moteur a turbine a gaz
US4379677A (en) * 1979-10-09 1983-04-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for adjusting the clearance between moving turbine blades and the turbine ring
FR2521217A1 (fr) * 1982-02-08 1983-08-12 Jehier Sa Perfectionnements aux anneaux isolants pour carters de turbines
US4462204A (en) * 1982-07-23 1984-07-31 General Electric Company Gas turbine engine cooling airflow modulator
EP0115984A1 (fr) * 1983-02-03 1984-08-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif d'étanchéité d'aubages mobiles de turbomachine
FR2557634A2 (fr) * 1983-02-03 1985-07-05 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine
US4551064A (en) * 1982-03-05 1985-11-05 Rolls-Royce Limited Turbine shroud and turbine shroud assembly
GB2168110A (en) * 1984-12-05 1986-06-11 United Technologies Corp Coolable stator assembly for a rotary machine
US4635332A (en) * 1985-09-13 1987-01-13 Solar Turbines Incorporated Sealed telescopic joint and method of assembly
US5116199A (en) * 1990-12-20 1992-05-26 General Electric Company Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion
US5178514A (en) * 1983-05-26 1993-01-12 Rolls-Royce Plc Cooling of gas turbine shroud rings
EP1041250A2 (de) 1999-04-01 2000-10-04 ABB Alstom Power (Schweiz) AG Hitzeschild für eine Gasturbine
EP1045115A1 (de) 1999-04-12 2000-10-18 Asea Brown Boveri AG Hitzeschild für eine Gasturbine
US6224329B1 (en) 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
EP1048822A3 (de) * 1999-04-29 2002-07-31 Alstom Hitzeschild für eine Gasturbine
US20030099541A1 (en) * 2001-11-29 2003-05-29 Ching-Pang Lee Article wall with interrupted ribbed heat transfer surface
US6733231B2 (en) * 2001-04-10 2004-05-11 Mitsubishi Heavy Industries, Ltd. Vapor tube structure of gas turbine
US20040219009A1 (en) * 2003-03-06 2004-11-04 Snecma Moteurs Turbomachine with cooled ring segments
EP1529926A2 (en) * 2003-11-04 2005-05-11 General Electric Company Spring and damper system for turbine shrouds
US20060115356A1 (en) * 2004-12-01 2006-06-01 Rolls-Royce Plc Casing arrangement
US20080050224A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US20080050225A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
EP2101041A2 (en) 2008-03-11 2009-09-16 United Technologies Corporation Cooling air manifold splash plate for a gas turbine engine
EP2180148A1 (de) * 2008-10-27 2010-04-28 Siemens Aktiengesellschaft Gasturbine mit Kühleinsatz
US20130014512A1 (en) * 2011-07-13 2013-01-17 United Technologies Corporation Ceramic Matrix Composite Combustor Vane Ring Assembly
US20130202422A1 (en) * 2010-03-26 2013-08-08 Kawasaki Jukogyo Kabushiki Kaisha Compressor of use in gas turbine engine
EP2657462A1 (en) * 2012-04-25 2013-10-30 General Electric Company Trubine Cooling System
CN104595036A (zh) * 2013-10-31 2015-05-06 空中客车运营简化股份公司 涡轮发动机的发动机室中的设备的热防护装置
EP3073061A1 (en) * 2015-03-16 2016-09-28 General Electric Company System for cooling a turbine shroud
CN106121738A (zh) * 2016-06-21 2016-11-16 中国航空工业集团公司沈阳发动机设计研究所 一种涡轮发动机静子叶片调节机构
EP3101228A1 (en) * 2015-05-08 2016-12-07 United Technologies Corporation Flow splitting baffle
US20160376921A1 (en) * 2015-06-29 2016-12-29 Rolls-Royce North American Technologies, Inc. Turbine shroud segment with integrated cooling air distribution system
EP3115565A1 (en) * 2015-06-29 2017-01-11 Rolls-Royce Corporation Turbine shroud segment with load distribution springs
US20170306785A1 (en) * 2016-04-25 2017-10-26 United Technologies Corporation Gas turbine engine having high pressure compressor case active clearance control system
US10094234B2 (en) 2015-06-29 2018-10-09 Rolls-Royce North America Technologies Inc. Turbine shroud segment with buffer air seal system
US20180363498A1 (en) * 2017-06-15 2018-12-20 General Electric Company Turbine shroud assembly
EP3514338A1 (en) * 2018-01-18 2019-07-24 Rolls-Royce plc Mount with cooling conduit for a gas turbine engine unit
US10577960B2 (en) 2015-06-29 2020-03-03 Rolls-Royce North American Technologies Inc. Turbine shroud segment with flange-facing perimeter seal
US20210301674A1 (en) * 2020-03-31 2021-09-30 Doosan Heavy Industries & Construction Co., Ltd. Apparatus for controlling turbine blade tip clearance and gas turbine including the same
US20220356806A1 (en) * 2021-05-04 2022-11-10 Raytheon Technologies Corporation Spring for radially stacked assemblies

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2617024C2 (de) * 1976-04-17 1985-09-26 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gasturbinentriebwerk
US4157232A (en) * 1977-10-31 1979-06-05 General Electric Company Turbine shroud support
CH633346A5 (de) * 1978-03-29 1982-11-30 Bbc Brown Boveri & Cie Leitschaufeltraeger an einer gasturbine.
US4251185A (en) * 1978-05-01 1981-02-17 Caterpillar Tractor Co. Expansion control ring for a turbine shroud assembly
GB2316134B (en) * 1982-02-12 1998-07-01 Rolls Royce Improvements in or relating to gas turbine engines
FR2535795B1 (fr) * 1982-11-08 1987-04-10 Snecma Dispositif de suspension d'aubes statoriques de compresseur axial pour le controle actif des jeux entre rotor et stator
FR2540938B1 (fr) * 1983-02-10 1987-06-05 Snecma Anneau de turbine d'une turbomachine
FR2869944B1 (fr) * 2004-05-04 2006-08-11 Snecma Moteurs Sa Dispositif de refroidissement pour anneau fixe de turbine a gaz
DE102006010863B4 (de) * 2005-03-24 2016-12-22 General Electric Technology Gmbh Turbomaschine, insbesondere Verdichter
US7665953B2 (en) * 2006-11-30 2010-02-23 General Electric Company Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies
FR3000985B1 (fr) * 2013-01-15 2017-02-17 Snecma Dispositif de refroidissement pour un carter de turbine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine
US3034298A (en) * 1958-06-12 1962-05-15 Gen Motors Corp Turbine cooling system
US3236069A (en) * 1962-11-23 1966-02-22 Scott & Williams Inc Knitted fabric
US3298823A (en) * 1966-02-08 1967-01-17 Grace W R & Co Method for the production of alloys
US3451215A (en) * 1967-04-03 1969-06-24 Gen Electric Fluid impingement starting means

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine
US3034298A (en) * 1958-06-12 1962-05-15 Gen Motors Corp Turbine cooling system
US3236069A (en) * 1962-11-23 1966-02-22 Scott & Williams Inc Knitted fabric
US3298823A (en) * 1966-02-08 1967-01-17 Grace W R & Co Method for the production of alloys
US3451215A (en) * 1967-04-03 1969-06-24 Gen Electric Fluid impingement starting means

Cited By (82)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USB563412I5 (xx) * 1975-03-28 1976-02-24
US3992127A (en) * 1975-03-28 1976-11-16 Westinghouse Electric Corporation Stator vane assembly for gas turbines
US4019320A (en) * 1975-12-05 1977-04-26 United Technologies Corporation External gas turbine engine cooling for clearance control
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
FR2371575A1 (fr) * 1976-11-22 1978-06-16 Gen Electric Structure de virole de turbine a gaz
FR2428141A1 (fr) * 1978-06-05 1980-01-04 Gen Electric Dispositif perfectionne de support de virole de turbine
FR2450344A1 (fr) * 1979-02-28 1980-09-26 Mtu Muenchen Gmbh Dispositif pour reduire au minimum et maintenir constants les jeux a la crete des aubes existants dans les turbines axiales, notamment pour turbomachines a gaz
FR2450345A1 (fr) * 1979-02-28 1980-09-26 Mtu Muenchen Gmbh Dispositif pour reduire au minimum et maintenir constants des jeux existant dans les turbines axiales, notamment turbomachines a gaz
US4317646A (en) * 1979-04-26 1982-03-02 Rolls-Royce Limited Gas turbine engines
US4379677A (en) * 1979-10-09 1983-04-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for adjusting the clearance between moving turbine blades and the turbine ring
FR2509373A1 (fr) * 1981-07-11 1983-01-14 Rolls Royce Couronne enveloppante reglable pour aubes mobiles de moteur a turbine a gaz
FR2521217A1 (fr) * 1982-02-08 1983-08-12 Jehier Sa Perfectionnements aux anneaux isolants pour carters de turbines
US4551064A (en) * 1982-03-05 1985-11-05 Rolls-Royce Limited Turbine shroud and turbine shroud assembly
US4462204A (en) * 1982-07-23 1984-07-31 General Electric Company Gas turbine engine cooling airflow modulator
EP0115984A1 (fr) * 1983-02-03 1984-08-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif d'étanchéité d'aubages mobiles de turbomachine
FR2557634A2 (fr) * 1983-02-03 1985-07-05 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine
US5178514A (en) * 1983-05-26 1993-01-12 Rolls-Royce Plc Cooling of gas turbine shroud rings
GB2168110A (en) * 1984-12-05 1986-06-11 United Technologies Corp Coolable stator assembly for a rotary machine
US4635332A (en) * 1985-09-13 1987-01-13 Solar Turbines Incorporated Sealed telescopic joint and method of assembly
US5116199A (en) * 1990-12-20 1992-05-26 General Electric Company Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion
US6224329B1 (en) 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
US6361273B1 (en) 1999-04-01 2002-03-26 Alstom (Switzerland) Ltd Heat shield for a gas turbine
EP1041250A2 (de) 1999-04-01 2000-10-04 ABB Alstom Power (Schweiz) AG Hitzeschild für eine Gasturbine
EP1045115A1 (de) 1999-04-12 2000-10-18 Asea Brown Boveri AG Hitzeschild für eine Gasturbine
EP1048822A3 (de) * 1999-04-29 2002-07-31 Alstom Hitzeschild für eine Gasturbine
US6733231B2 (en) * 2001-04-10 2004-05-11 Mitsubishi Heavy Industries, Ltd. Vapor tube structure of gas turbine
US20030099541A1 (en) * 2001-11-29 2003-05-29 Ching-Pang Lee Article wall with interrupted ribbed heat transfer surface
US6612808B2 (en) * 2001-11-29 2003-09-02 General Electric Company Article wall with interrupted ribbed heat transfer surface
US20040219009A1 (en) * 2003-03-06 2004-11-04 Snecma Moteurs Turbomachine with cooled ring segments
US7011493B2 (en) * 2003-03-06 2006-03-14 Snecma Moteurs Turbomachine with cooled ring segments
EP1529926A3 (en) * 2003-11-04 2012-08-22 General Electric Company Spring and damper system for turbine shrouds
EP1529926A2 (en) * 2003-11-04 2005-05-11 General Electric Company Spring and damper system for turbine shrouds
US20060115356A1 (en) * 2004-12-01 2006-06-01 Rolls-Royce Plc Casing arrangement
US7140836B2 (en) 2004-12-01 2006-11-28 Rolls Royce Plc Casing arrangement
GB2420830B (en) * 2004-12-01 2007-01-03 Rolls Royce Plc Improved casing arrangement
GB2420830A (en) * 2004-12-01 2006-06-07 Rolls Royce Plc Casing arrangement
US20080050224A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US20080050225A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US7658593B2 (en) 2005-03-24 2010-02-09 Alstom Technology Ltd Heat accumulation segment
US7665958B2 (en) 2005-03-24 2010-02-23 Alstom Technology Ltd. Heat accumulation segment
EP2101041A2 (en) 2008-03-11 2009-09-16 United Technologies Corporation Cooling air manifold splash plate for a gas turbine engine
EP2101041A3 (en) * 2008-03-11 2012-10-24 United Technologies Corporation Cooling air manifold splash plate for a gas turbine engine
EP2180148A1 (de) * 2008-10-27 2010-04-28 Siemens Aktiengesellschaft Gasturbine mit Kühleinsatz
WO2010049195A1 (de) * 2008-10-27 2010-05-06 Siemens Aktiengesellschaft Gasturbine mit kühleinsatz
CN102197195A (zh) * 2008-10-27 2011-09-21 西门子公司 具有冷却嵌件的燃气涡轮机
US9534607B2 (en) * 2010-03-26 2017-01-03 Kawasaki Jukogyo Kabushiki Kaisha Compressor of use in gas turbine engine
US20130202422A1 (en) * 2010-03-26 2013-08-08 Kawasaki Jukogyo Kabushiki Kaisha Compressor of use in gas turbine engine
US20130014512A1 (en) * 2011-07-13 2013-01-17 United Technologies Corporation Ceramic Matrix Composite Combustor Vane Ring Assembly
US9335051B2 (en) * 2011-07-13 2016-05-10 United Technologies Corporation Ceramic matrix composite combustor vane ring assembly
EP2657462A1 (en) * 2012-04-25 2013-10-30 General Electric Company Trubine Cooling System
CN103375204A (zh) * 2012-04-25 2013-10-30 通用电气公司 涡轮冷却系统
US20130283814A1 (en) * 2012-04-25 2013-10-31 General Electric Company Turbine cooling system
CN104595036A (zh) * 2013-10-31 2015-05-06 空中客车运营简化股份公司 涡轮发动机的发动机室中的设备的热防护装置
EP2868870A1 (fr) * 2013-10-31 2015-05-06 Airbus Operations Turbomachine accueillant un équipement dans son compartiment moteur ainsi qu'un dispositif de protection thermique de l'équipement
CN104595036B (zh) * 2013-10-31 2018-11-23 空中客车运营简化股份公司 涡轮发动机的发动机室中的设备的热防护装置
US10422244B2 (en) 2015-03-16 2019-09-24 General Electric Company System for cooling a turbine shroud
CN105986847B (zh) * 2015-03-16 2022-05-31 通用电气公司 用于冷却涡轮护罩的系统
EP3073061A1 (en) * 2015-03-16 2016-09-28 General Electric Company System for cooling a turbine shroud
CN105986847A (zh) * 2015-03-16 2016-10-05 通用电气公司 用于冷却涡轮护罩的系统
US9926789B2 (en) 2015-05-08 2018-03-27 United Technologies Corporation Flow splitting baffle
EP3101228A1 (en) * 2015-05-08 2016-12-07 United Technologies Corporation Flow splitting baffle
US10876422B2 (en) 2015-06-29 2020-12-29 Rolls-Royce North American Technologies Inc. Turbine shroud segment with buffer air seal system
US10577960B2 (en) 2015-06-29 2020-03-03 Rolls-Royce North American Technologies Inc. Turbine shroud segment with flange-facing perimeter seal
US20160376921A1 (en) * 2015-06-29 2016-12-29 Rolls-Royce North American Technologies, Inc. Turbine shroud segment with integrated cooling air distribution system
US10094234B2 (en) 2015-06-29 2018-10-09 Rolls-Royce North America Technologies Inc. Turbine shroud segment with buffer air seal system
EP3115559A1 (en) * 2015-06-29 2017-01-11 Rolls-Royce Corporation Turbine shroud segment with integrated cooling air distribution system
US11280206B2 (en) 2015-06-29 2022-03-22 Rolls-Royce North American Technologies Inc. Turbine shroud segment with flange-facing perimeter seal
US10184352B2 (en) * 2015-06-29 2019-01-22 Rolls-Royce North American Technologies Inc. Turbine shroud segment with integrated cooling air distribution system
US10196919B2 (en) 2015-06-29 2019-02-05 Rolls-Royce North American Technologies Inc. Turbine shroud segment with load distribution springs
US10934879B2 (en) 2015-06-29 2021-03-02 Rolls-Royce North American Technologies Inc. Turbine shroud segment with load distribution springs
EP3115565A1 (en) * 2015-06-29 2017-01-11 Rolls-Royce Corporation Turbine shroud segment with load distribution springs
EP3239476A1 (en) * 2016-04-25 2017-11-01 United Technologies Corporation Case clearance control system and corresponding gas turbine engines
US10801354B2 (en) * 2016-04-25 2020-10-13 Raytheon Technologies Corporation Gas turbine engine having high pressure compressor case active clearance control system
US20170306785A1 (en) * 2016-04-25 2017-10-26 United Technologies Corporation Gas turbine engine having high pressure compressor case active clearance control system
CN106121738A (zh) * 2016-06-21 2016-11-16 中国航空工业集团公司沈阳发动机设计研究所 一种涡轮发动机静子叶片调节机构
US10544701B2 (en) * 2017-06-15 2020-01-28 General Electric Company Turbine shroud assembly
US20180363498A1 (en) * 2017-06-15 2018-12-20 General Electric Company Turbine shroud assembly
EP3514338A1 (en) * 2018-01-18 2019-07-24 Rolls-Royce plc Mount with cooling conduit for a gas turbine engine unit
US20210301674A1 (en) * 2020-03-31 2021-09-30 Doosan Heavy Industries & Construction Co., Ltd. Apparatus for controlling turbine blade tip clearance and gas turbine including the same
US11634996B2 (en) * 2020-03-31 2023-04-25 Doosan Enerbility Co., Ltd. Apparatus for controlling turbine blade tip clearance and gas turbine including the same
US20220356806A1 (en) * 2021-05-04 2022-11-10 Raytheon Technologies Corporation Spring for radially stacked assemblies
US11512604B1 (en) * 2021-05-04 2022-11-29 Raytheon Technologies Corporation Spring for radially stacked assemblies

Also Published As

Publication number Publication date
GB1463344A (en) 1977-02-02
SE7409739L (xx) 1975-01-28
JPS5322601B2 (xx) 1978-07-10
FR2238838A1 (xx) 1975-02-21
JPS5043308A (xx) 1975-04-19
IT1015601B (it) 1977-05-20
NL7409533A (nl) 1975-01-29
CA995140A (en) 1976-08-17
FR2238838B1 (xx) 1981-05-29
SE385493B (sv) 1976-07-05
DE2432092A1 (de) 1975-02-06
CH583849A5 (xx) 1977-01-14

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