EP2264282A3 - Cooled gas turbine stator assembly - Google Patents

Cooled gas turbine stator assembly Download PDF

Info

Publication number
EP2264282A3
EP2264282A3 EP10250997.3A EP10250997A EP2264282A3 EP 2264282 A3 EP2264282 A3 EP 2264282A3 EP 10250997 A EP10250997 A EP 10250997A EP 2264282 A3 EP2264282 A3 EP 2264282A3
Authority
EP
European Patent Office
Prior art keywords
gas path
annular cavity
path platform
stator assembly
nozzle
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.)
Withdrawn
Application number
EP10250997.3A
Other languages
German (de)
French (fr)
Other versions
EP2264282A2 (en
Inventor
Cheng-Zhang Wang
Robert M. Sonntag
Wiliam A. Daniel
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies 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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2264282A2 publication Critical patent/EP2264282A2/en
Publication of EP2264282A3 publication Critical patent/EP2264282A3/en
Withdrawn legal-status Critical Current

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Abstract

A stator assembly (100) for a gas turbine engine is provided having an annular body (10), an inner gas path platform (30), a plurality of fairings (20), and at least one nozzle (50). The annular body (10) has an outer gas path platform (12) and a circumferentially extending annular cavity (14) disposed radially outside of the outer gas path platform (12). The fairings (20) extend radially between the inner gas path platform (30) and the outer gas path platform (12). Each fairing (20) includes a gas passage (22) extending from the annular cavity (14) through the inner gas path platform (30). The at least one nozzle (50) has an inlet orifice (52) disposed outside of the annular cavity (14) and an exit orifice (54) disposed within the annular cavity (14). The exit orifice (54) is oriented within the annular cavity (14) such that cooling air exiting the nozzle (50) travels in a substantially circumferential direction within the annular cavity (14).
EP10250997.3A 2009-05-29 2010-05-28 Cooled gas turbine stator assembly Withdrawn EP2264282A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/474,822 US20100303610A1 (en) 2009-05-29 2009-05-29 Cooled gas turbine stator assembly

Publications (2)

Publication Number Publication Date
EP2264282A2 EP2264282A2 (en) 2010-12-22
EP2264282A3 true EP2264282A3 (en) 2013-10-23

Family

ID=42729427

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10250997.3A Withdrawn EP2264282A3 (en) 2009-05-29 2010-05-28 Cooled gas turbine stator assembly

Country Status (2)

Country Link
US (1) US20100303610A1 (en)
EP (1) EP2264282A3 (en)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9279341B2 (en) * 2011-09-22 2016-03-08 Pratt & Whitney Canada Corp. Air system architecture for a mid-turbine frame module
US8932011B2 (en) 2011-10-06 2015-01-13 United Technologies Corporation Shaft assembly for a gas turbine engine
US9316117B2 (en) 2012-01-30 2016-04-19 United Technologies Corporation Internally cooled spoke
US9217371B2 (en) 2012-07-13 2015-12-22 United Technologies Corporation Mid-turbine frame with tensioned spokes
US9222413B2 (en) * 2012-07-13 2015-12-29 United Technologies Corporation Mid-turbine frame with threaded spokes
US9587514B2 (en) 2012-07-13 2017-03-07 United Technologies Corporation Vane insertable tie rods with keyed connections
US9010122B2 (en) 2012-07-27 2015-04-21 United Technologies Corporation Turbine engine combustor and stator vane assembly
US20140186160A1 (en) * 2012-12-29 2014-07-03 United Technologies Corporation Slider seal
US9617870B2 (en) 2013-02-05 2017-04-11 United Technologies Corporation Bracket for mounting a stator guide vane arrangement to a strut in a turbine engine
EP2971612B1 (en) * 2013-03-13 2018-01-31 United Technologies Corporation Engine mid-turbine frame transfer tube for low pressure turbine case cooling
GB201305432D0 (en) 2013-03-26 2013-05-08 Rolls Royce Plc A gas turbine engine cooling arrangement
US9803501B2 (en) * 2014-02-14 2017-10-31 United Technologies Corporation Engine mid-turbine frame distributive coolant flow
ES2716100T3 (en) 2014-06-12 2019-06-10 MTU Aero Engines AG Intermediate housing for a gas turbine and gas turbine with said intermediate housing
US10392969B2 (en) 2014-12-02 2019-08-27 United Technologies Corporation Moment accommodating fastener assembly
US9856750B2 (en) * 2015-01-16 2018-01-02 United Technologies Corporation Cooling passages for a mid-turbine frame
US9732628B2 (en) * 2015-03-20 2017-08-15 United Technologies Corporation Cooling passages for a mid-turbine frame
CN107849925B (en) * 2015-07-06 2020-03-17 西门子股份公司 Turbine stator and/or rotor blades with cooling flow regulation features and corresponding method of adapting blades
US10443449B2 (en) 2015-07-24 2019-10-15 Pratt & Whitney Canada Corp. Spoke mounting arrangement
CN107849937B (en) 2015-07-24 2020-06-19 普拉特-惠特尼加拿大公司 Turbine mid-frame spoke cooling system and method
US10247035B2 (en) 2015-07-24 2019-04-02 Pratt & Whitney Canada Corp. Spoke locking architecture
DE102015215144B4 (en) * 2015-08-07 2017-11-09 MTU Aero Engines AG Device and method for influencing the temperatures in inner ring segments of a gas turbine
US10273812B2 (en) 2015-12-18 2019-04-30 Pratt & Whitney Canada Corp. Turbine rotor coolant supply system
US11549396B2 (en) 2019-11-12 2023-01-10 Pratt & Whitney Canada Corp. Mid-turbine frame for gas turbine engine
US11698005B2 (en) 2020-02-07 2023-07-11 Raytheon Technologies Corporation Flow diverter for mid-turbine frame cooling air delivery
CN114198153A (en) * 2020-09-17 2022-03-18 中国航发商用航空发动机有限责任公司 Turbine blade cooling system and aircraft engine
US11473439B1 (en) * 2021-09-23 2022-10-18 General Electric Company Gas turbine engine with hollow rotor in fluid communication with a balance piston cavity

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4979872A (en) * 1989-06-22 1990-12-25 United Technologies Corporation Bearing compartment support
US5273397A (en) * 1993-01-13 1993-12-28 General Electric Company Turbine casing and radiation shield
US5609467A (en) * 1995-09-28 1997-03-11 Cooper Cameron Corporation Floating interturbine duct assembly for high temperature power turbine
US6508620B2 (en) * 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
EP1526251A1 (en) * 2003-10-22 2005-04-27 General Electric Company Turbine nozzle cooling configuration
US7273345B2 (en) * 2003-11-07 2007-09-25 Alstom Technology Ltd Method for operating a turbo engine and turbo engine
US7373773B2 (en) * 2003-09-04 2008-05-20 Hitachi, Ltd. Gas turbine installation, cooling air supplying method and method of modifying a gas turbine installation
EP1980723A2 (en) * 2007-04-12 2008-10-15 United Technologies Corporation Out-flow margin protection for a gas turbine engine
US20080310949A1 (en) * 2004-07-28 2008-12-18 Mitsubishi Heavy Industries, Ltd. Casing and Gas Turbine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4478551A (en) * 1981-12-08 1984-10-23 United Technologies Corporation Turbine exhaust case design
US4770608A (en) * 1985-12-23 1988-09-13 United Technologies Corporation Film cooled vanes and turbines
US4767268A (en) * 1987-08-06 1988-08-30 United Technologies Corporation Triple pass cooled airfoil
US4890978A (en) * 1988-10-19 1990-01-02 Westinghouse Electric Corp. Method and apparatus for vane segment support and alignment in combustion turbines
US5117626A (en) * 1990-09-04 1992-06-02 Westinghouse Electric Corp. Apparatus for cooling rotating blades in a gas turbine
US5141394A (en) * 1990-10-10 1992-08-25 Westinghouse Electric Corp. Apparatus and method for supporting a vane segment in a gas turbine
US5387086A (en) * 1993-07-19 1995-02-07 General Electric Company Gas turbine blade with improved cooling
US5498126A (en) * 1994-04-28 1996-03-12 United Technologies Corporation Airfoil with dual source cooling
DE19549202B4 (en) * 1995-12-30 2006-05-04 Robert Bosch Gmbh Rectifier diode
US5741117A (en) * 1996-10-22 1998-04-21 United Technologies Corporation Method for cooling a gas turbine stator vane
US5702214A (en) * 1996-11-07 1997-12-30 Avibank Mfg., Inc. Non-removable structural fastener assembly
US5848874A (en) * 1997-05-13 1998-12-15 United Technologies Corporation Gas turbine stator vane assembly
FR2914017B1 (en) * 2007-03-20 2011-07-08 Snecma SEALING DEVICE FOR A COOLING CIRCUIT, INTER-TURBINE HOUSING BEING EQUIPPED AND TURBOREACTOR COMPRISING THE SAME

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4979872A (en) * 1989-06-22 1990-12-25 United Technologies Corporation Bearing compartment support
US5273397A (en) * 1993-01-13 1993-12-28 General Electric Company Turbine casing and radiation shield
US5609467A (en) * 1995-09-28 1997-03-11 Cooper Cameron Corporation Floating interturbine duct assembly for high temperature power turbine
US6508620B2 (en) * 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
US7373773B2 (en) * 2003-09-04 2008-05-20 Hitachi, Ltd. Gas turbine installation, cooling air supplying method and method of modifying a gas turbine installation
EP1526251A1 (en) * 2003-10-22 2005-04-27 General Electric Company Turbine nozzle cooling configuration
US7273345B2 (en) * 2003-11-07 2007-09-25 Alstom Technology Ltd Method for operating a turbo engine and turbo engine
US20080310949A1 (en) * 2004-07-28 2008-12-18 Mitsubishi Heavy Industries, Ltd. Casing and Gas Turbine
EP1980723A2 (en) * 2007-04-12 2008-10-15 United Technologies Corporation Out-flow margin protection for a gas turbine engine

Also Published As

Publication number Publication date
EP2264282A2 (en) 2010-12-22
US20100303610A1 (en) 2010-12-02

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