CN203879556U - 用于从涡轮机排除热量的系统 - Google Patents

用于从涡轮机排除热量的系统 Download PDF

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Publication number
CN203879556U
CN203879556U CN201320808745.1U CN201320808745U CN203879556U CN 203879556 U CN203879556 U CN 203879556U CN 201320808745 U CN201320808745 U CN 201320808745U CN 203879556 U CN203879556 U CN 203879556U
Authority
CN
China
Prior art keywords
substrate
fluid
fluid channel
coating
airfoil
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
CN201320808745.1U
Other languages
English (en)
Chinese (zh)
Inventor
G.M.伊策尔
K.R.柯特利
C.L.范德沃尔特
R.S.班克
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Application granted granted Critical
Publication of CN203879556U publication Critical patent/CN203879556U/zh
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
CN201320808745.1U 2012-12-10 2013-12-10 用于从涡轮机排除热量的系统 Expired - Lifetime CN203879556U (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/709,306 US9297267B2 (en) 2012-12-10 2012-12-10 System and method for removing heat from a turbine
US13/709306 2012-12-10

Publications (1)

Publication Number Publication Date
CN203879556U true CN203879556U (zh) 2014-10-15

Family

ID=49712934

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201320808745.1U Expired - Lifetime CN203879556U (zh) 2012-12-10 2013-12-10 用于从涡轮机排除热量的系统

Country Status (4)

Country Link
US (1) US9297267B2 (https=)
EP (1) EP2740900A3 (https=)
JP (1) JP2014114814A (https=)
CN (1) CN203879556U (https=)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106930788A (zh) * 2015-10-15 2017-07-07 通用电气公司 涡轮叶片

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10731472B2 (en) * 2016-05-10 2020-08-04 General Electric Company Airfoil with cooling circuit
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10641108B2 (en) * 2018-04-06 2020-05-05 United Technologies Corporation Turbine blade shroud for gas turbine engine with power turbine and method of manufacturing same
US10711621B1 (en) 2019-02-01 2020-07-14 Rolls-Royce Plc Turbine vane assembly with ceramic matrix composite components and temperature management features
US10767495B2 (en) 2019-02-01 2020-09-08 Rolls-Royce Plc Turbine vane assembly with cooling feature
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Family Cites Families (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1190480A (en) * 1981-03-02 1985-07-16 Westinghouse Electric Corporation Vane structure having improved cooled operation in stationary combustion turbines
CA1193551A (en) * 1981-12-31 1985-09-17 Paul C. Holden Shell-spar cooled airfoil having variable coolant passageway area
JP3015531B2 (ja) * 1991-09-06 2000-03-06 株式会社東芝 ガスタービン
US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
US5611197A (en) 1995-10-23 1997-03-18 General Electric Company Closed-circuit air cooled turbine
JPH09303103A (ja) * 1996-05-16 1997-11-25 Toshiba Corp 閉ループ冷却形タービン動翼
JPH1047005A (ja) * 1996-07-30 1998-02-17 Toshiba Corp ガスタービンの冷却翼
JPH10280908A (ja) * 1997-04-09 1998-10-20 Toshiba Corp ガスタービンの静翼
US5813827A (en) * 1997-04-15 1998-09-29 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil
JPH10306701A (ja) * 1997-05-08 1998-11-17 Toshiba Corp タービン動翼およびその製造方法
US6059529A (en) * 1998-03-16 2000-05-09 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device
JP4339520B2 (ja) * 1998-09-24 2009-10-07 シーメンス アクチエンゲゼルシヤフト ガスタービンにおける燃料の予熱方法
US6165600A (en) 1998-10-06 2000-12-26 General Electric Company Gas turbine engine component having a thermal-insulating multilayer ceramic coating
US6261054B1 (en) 1999-01-25 2001-07-17 General Electric Company Coolable airfoil assembly
US6174133B1 (en) 1999-01-25 2001-01-16 General Electric Company Coolable airfoil
US6206638B1 (en) * 1999-02-12 2001-03-27 General Electric Company Low cost airfoil cooling circuit with sidewall impingement cooling chambers
US6413040B1 (en) * 2000-06-13 2002-07-02 General Electric Company Support pedestals for interconnecting a cover and nozzle band wall in a gas turbine nozzle segment
US6617003B1 (en) 2000-11-06 2003-09-09 General Electric Company Directly cooled thermal barrier coating system
US6528118B2 (en) 2001-02-06 2003-03-04 General Electric Company Process for creating structured porosity in thermal barrier coating
US6551061B2 (en) 2001-03-27 2003-04-22 General Electric Company Process for forming micro cooling channels inside a thermal barrier coating system without masking material
US6921014B2 (en) * 2002-05-07 2005-07-26 General Electric Company Method for forming a channel on the surface of a metal substrate
US6905302B2 (en) 2003-09-17 2005-06-14 General Electric Company Network cooled coated wall
US7217092B2 (en) * 2004-04-14 2007-05-15 General Electric Company Method and apparatus for reducing turbine blade temperatures
US7137782B2 (en) * 2004-04-27 2006-11-21 General Electric Company Turbulator on the underside of a turbine blade tip turn and related method
US8651805B2 (en) * 2010-04-22 2014-02-18 General Electric Company Hot gas path component cooling system
US8387245B2 (en) 2010-11-10 2013-03-05 General Electric Company Components with re-entrant shaped cooling channels and methods of manufacture
US20120114868A1 (en) 2010-11-10 2012-05-10 General Electric Company Method of fabricating a component using a fugitive coating
US8673397B2 (en) 2010-11-10 2014-03-18 General Electric Company Methods of fabricating and coating a component
US8739404B2 (en) 2010-11-23 2014-06-03 General Electric Company Turbine components with cooling features and methods of manufacturing the same
US8727727B2 (en) 2010-12-10 2014-05-20 General Electric Company Components with cooling channels and methods of manufacture
US20120148769A1 (en) 2010-12-13 2012-06-14 General Electric Company Method of fabricating a component using a two-layer structural coating
US8753071B2 (en) 2010-12-22 2014-06-17 General Electric Company Cooling channel systems for high-temperature components covered by coatings, and related processes

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106930788A (zh) * 2015-10-15 2017-07-07 通用电气公司 涡轮叶片
CN106930788B (zh) * 2015-10-15 2019-04-05 通用电气公司 涡轮叶片

Also Published As

Publication number Publication date
EP2740900A3 (en) 2018-03-14
EP2740900A2 (en) 2014-06-11
JP2014114814A (ja) 2014-06-26
US9297267B2 (en) 2016-03-29
US20140157792A1 (en) 2014-06-12

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C14 Grant of patent or utility model
GR01 Patent grant
CX01 Expiry of patent term

Granted publication date: 20141015

CX01 Expiry of patent term