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GB1359983A - Cooled guide blades for gas turbines - Google Patents

Cooled guide blades for gas turbines

Info

Publication number
GB1359983A
GB1359983A GB247973A GB247973A GB1359983A GB 1359983 A GB1359983 A GB 1359983A GB 247973 A GB247973 A GB 247973A GB 247973 A GB247973 A GB 247973A GB 1359983 A GB1359983 A GB 1359983A
Authority
GB
United Kingdom
Prior art keywords
chamber
duct
exit
trailing edge
blade
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
Application number
GB247973A
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.)
Brown Boveri Sulzer Turbomaschinen AG
Original Assignee
Brown Boveri Sulzer Turbomaschinen AG
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 Brown Boveri Sulzer Turbomaschinen AG filed Critical Brown Boveri Sulzer Turbomaschinen AG
Publication of GB1359983A publication Critical patent/GB1359983A/en
Expired 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
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Landscapes

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

Abstract

1359983 Turbine blades BROWN BOVERISULZER TURBOMACHINERY Ltd 17 Jan 1973 [18 Jan 1972] 2479/73 Heading FIT A gas turbine guide blade is provided with two cooling air-flow paths, a first path extending from a chamber 13 within platform 14, along leading edge duct 15 to second chamber 16 within platform 17 at the other end of the blade, chamber 16 communicating with an exit 18 adjacent trailing edge 19, and a second path extending from chamber 13 to a second exit 24 also adjacent trailing edge 19. The second path comprises a duct 20 of greater cross-section than duct 15 and connecting via chamber 21 with a duct 22 having fins 25, duct 22 connecting via chamber 23 with exit 24. A transverse partition 26 separates exits 18, 24, the latter including fins 30. Exits 18, 24 may discharge immediately at trailing edge 19 or to one or other side thereof Figs. 2 to 4 (not shown). The blade is formed by casting, plates 27, 28, 29 being subsequently welded in position.
GB247973A 1972-01-18 1973-01-17 Cooled guide blades for gas turbines Expired GB1359983A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH69972 1972-01-18

Publications (1)

Publication Number Publication Date
GB1359983A true GB1359983A (en) 1974-07-17

Family

ID=4193097

Family Applications (1)

Application Number Title Priority Date Filing Date
GB247973A Expired GB1359983A (en) 1972-01-18 1973-01-17 Cooled guide blades for gas turbines

Country Status (11)

Country Link
US (1) US3807892A (en)
JP (1) JPS5145726B2 (en)
BE (1) BE794195A (en)
CA (1) CA967095A (en)
CH (1) CH547431A (en)
DE (1) DE2202858C2 (en)
FR (1) FR2168802A5 (en)
GB (1) GB1359983A (en)
IT (1) IT978243B (en)
NL (1) NL164358C (en)
SE (1) SE381311B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2345942A (en) * 1998-12-24 2000-07-26 Rolls Royce Plc Gas turbine engine blade cooling air system
GB2366600A (en) * 2000-09-09 2002-03-13 Rolls Royce Plc Cooling arrangement for trailing edge of aerofoil

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CH580750A5 (en) * 1974-07-17 1976-10-15 Bbc Sulzer Turbomaschinen
CH582305A5 (en) * 1974-09-05 1976-11-30 Bbc Sulzer Turbomaschinen
US4025226A (en) * 1975-10-03 1977-05-24 United Technologies Corporation Air cooled turbine vane
US4236870A (en) * 1977-12-27 1980-12-02 United Technologies Corporation Turbine blade
US4278400A (en) * 1978-09-05 1981-07-14 United Technologies Corporation Coolable rotor blade
JPS5540221A (en) * 1978-09-14 1980-03-21 Hitachi Ltd Cooling structure of gas turbin blade
US4303374A (en) * 1978-12-15 1981-12-01 General Electric Company Film cooled airfoil body
JPS6056883B2 (en) * 1979-02-28 1985-12-12 株式会社東芝 gas turbine moving blades
GB2100807B (en) * 1981-06-30 1984-08-01 Rolls Royce Turbine blade for gas turbine engines
GB2163218B (en) * 1981-07-07 1986-07-16 Rolls Royce Cooled vane or blade for a gas turbine engine
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
US4753575A (en) * 1987-08-06 1988-06-28 United Technologies Corporation Airfoil with nested cooling channels
US4767268A (en) * 1987-08-06 1988-08-30 United Technologies Corporation Triple pass cooled airfoil
US5030060A (en) * 1988-10-20 1991-07-09 The United States Of America As Represented By The Secretary Of The Air Force Method and apparatus for cooling high temperature ceramic turbine blade portions
FR2678318B1 (en) * 1991-06-25 1993-09-10 Snecma COOLED VANE OF TURBINE DISTRIBUTOR.
FR2681095B1 (en) * 1991-09-05 1993-11-19 Snecma CARENE TURBINE DISTRIBUTOR.
US5591002A (en) * 1994-08-23 1997-01-07 General Electric Co. Closed or open air cooling circuits for nozzle segments with wheelspace purge
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
US5503529A (en) * 1994-12-08 1996-04-02 General Electric Company Turbine blade having angled ejection slot
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
RU2151303C1 (en) * 1996-03-14 2000-06-20 АББ Унитурбо Лтд. Cooled moving or nozzle blade of gas turbine
US5741117A (en) * 1996-10-22 1998-04-21 United Technologies Corporation Method for cooling a gas turbine stator vane
JP3426902B2 (en) * 1997-03-11 2003-07-14 三菱重工業株式会社 Gas turbine cooling vane
US5902093A (en) * 1997-08-22 1999-05-11 General Electric Company Crack arresting rotor blade
DE59907300D1 (en) 1998-04-21 2003-11-13 Siemens Ag TURBINE BLADE
EP1099825A1 (en) * 1999-11-12 2001-05-16 Siemens Aktiengesellschaft Turbine blade and production method therefor
US6343911B1 (en) * 2000-04-05 2002-02-05 General Electric Company Side wall cooling for nozzle segments for a gas turbine
US6453557B1 (en) * 2000-04-11 2002-09-24 General Electric Company Method of joining a vane cavity insert to a nozzle segment of a gas turbine
US6386825B1 (en) * 2000-04-11 2002-05-14 General Electric Company Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment
US6419445B1 (en) * 2000-04-11 2002-07-16 General Electric Company Apparatus for impingement cooling a side wall adjacent an undercut region of a turbine nozzle segment
US6375415B1 (en) * 2000-04-25 2002-04-23 General Electric Company Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment
US6439837B1 (en) * 2000-06-27 2002-08-27 General Electric Company Nozzle braze backside cooling
US6454526B1 (en) * 2000-09-28 2002-09-24 Siemens Westinghouse Power Corporation Cooled turbine vane with endcaps
RU2188323C1 (en) * 2001-02-21 2002-08-27 "МАТИ" - Российский государственный технологический университет им. К.Э.Циолковского Gas turbine cooled blade
US6508620B2 (en) * 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
US6527514B2 (en) 2001-06-11 2003-03-04 Alstom (Switzerland) Ltd Turbine blade with rub tolerant cooling construction
US6634858B2 (en) * 2001-06-11 2003-10-21 Alstom (Switzerland) Ltd Gas turbine airfoil
EP1329593B1 (en) 2002-01-17 2005-03-23 Siemens Aktiengesellschaft Turbine blade with a hot gas suporting platform and a mechanical load suporting platform
FR2833298B1 (en) * 2001-12-10 2004-08-06 Snecma Moteurs IMPROVEMENTS TO THE THERMAL BEHAVIOR OF THE TRAILING EDGE OF A HIGH-PRESSURE TURBINE BLADE
RU2208683C1 (en) * 2002-01-08 2003-07-20 Ульяновский государственный технический университет Cooled blade of turbine
CH695702A5 (en) * 2002-01-15 2006-07-31 Alstom Technology Ltd Turbine vane, for a gas turbine, has inner cooling channels in a serpentine structure, with flow connections through hairpin bends
US6860108B2 (en) 2003-01-22 2005-03-01 Mitsubishi Heavy Industries, Ltd. Gas turbine tail tube seal and gas turbine using the same
US6969233B2 (en) * 2003-02-27 2005-11-29 General Electric Company Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity
US6984101B2 (en) * 2003-07-14 2006-01-10 Siemens Westinghouse Power Corporation Turbine vane plate assembly
US6929445B2 (en) * 2003-10-22 2005-08-16 General Electric Company Split flow turbine nozzle
US7029228B2 (en) * 2003-12-04 2006-04-18 General Electric Company Method and apparatus for convective cooling of side-walls of turbine nozzle segments
RU2276732C2 (en) * 2004-01-16 2006-05-20 Ульяновский государственный технический университет Turbine cooled blade
EP1571295A1 (en) * 2004-03-01 2005-09-07 ALSTOM Technology Ltd Cooled blade of a turbomachine and method of cooling
US7210906B2 (en) * 2004-08-10 2007-05-01 Pratt & Whitney Canada Corp. Internally cooled gas turbine airfoil and method
US7238003B2 (en) * 2004-08-24 2007-07-03 Pratt & Whitney Canada Corp. Vane attachment arrangement
US7189060B2 (en) * 2005-01-07 2007-03-13 Siemens Power Generation, Inc. Cooling system including mini channels within a turbine blade of a turbine engine
RU2425982C2 (en) * 2005-04-14 2011-08-10 Альстом Текнолоджи Лтд Gas turbine vane
US20090003987A1 (en) * 2006-12-21 2009-01-01 Jack Raul Zausner Airfoil with improved cooling slot arrangement
GB0813839D0 (en) 2008-07-30 2008-09-03 Rolls Royce Plc An aerofoil and method for making an aerofoil
EP2256297B8 (en) * 2009-05-19 2012-10-03 Alstom Technology Ltd Gas turbine vane with improved cooling
US8500392B2 (en) * 2009-10-01 2013-08-06 Pratt & Whitney Canada Corp. Sealing for vane segments
US8616834B2 (en) * 2010-04-30 2013-12-31 General Electric Company Gas turbine engine airfoil integrated heat exchanger
RU2439336C1 (en) * 2010-05-11 2012-01-10 Открытое акционерное общество "Авиадвигатель" Cooled blade of turbomachine
US8840369B2 (en) * 2010-09-30 2014-09-23 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8777568B2 (en) * 2010-09-30 2014-07-15 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US9145780B2 (en) 2011-12-15 2015-09-29 United Technologies Corporation Gas turbine engine airfoil cooling circuit
US9151164B2 (en) * 2012-03-21 2015-10-06 Pratt & Whitney Canada Corp. Dual-use of cooling air for turbine vane and method
WO2014009074A1 (en) * 2012-07-12 2014-01-16 Siemens Aktiengesellschaft Turbine blade for a gas turbine
US9359902B2 (en) 2013-06-28 2016-06-07 Siemens Energy, Inc. Turbine airfoil with ambient cooling system
RU2568763C2 (en) * 2014-01-30 2015-11-20 Альстом Текнолоджи Лтд Gas turbine component
US9771816B2 (en) * 2014-05-07 2017-09-26 General Electric Company Blade cooling circuit feed duct, exhaust duct, and related cooling structure
US20170234142A1 (en) * 2016-02-17 2017-08-17 General Electric Company Rotor Blade Trailing Edge Cooling
US10156146B2 (en) * 2016-04-25 2018-12-18 General Electric Company Airfoil with variable slot decoupling
KR101882104B1 (en) * 2016-12-20 2018-07-25 두산중공업 주식회사 Gas turbine
US20200024967A1 (en) * 2018-07-20 2020-01-23 United Technologies Corporation Airfoil having angled trailing edge slots
US11028700B2 (en) * 2018-11-09 2021-06-08 Raytheon Technologies Corporation Airfoil with cooling passage circuit through platforms and airfoil section
EP3862537A1 (en) * 2020-02-10 2021-08-11 General Electric Company Polska sp. z o.o. Cooled turbine nozzle and nozzle segment
GB202117857D0 (en) * 2021-12-10 2022-01-26 Rolls Royce Plc Vane assembly for a gas turbine engine
CN115075891A (en) * 2022-05-29 2022-09-20 中国船舶重工集团公司第七0三研究所 Air-cooled turbine guide vane trailing edge structure with pressure side exhaust
GB2633337A (en) * 2023-09-06 2025-03-12 Siemens Energy Global Gmbh & Co Kg Turbine component for gas turbine engine
CN118622391B (en) * 2024-04-17 2025-10-31 南京玻璃纤维研究设计院有限公司 Method for manufacturing aeronautical air-cooled turbine guide vane preform with multi-channel blade body

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US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3533711A (en) * 1966-02-26 1970-10-13 Gen Electric Cooled vane structure for high temperature turbines
US3623825A (en) * 1969-11-13 1971-11-30 Avco Corp Liquid-metal-filled rotor blade

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2345942A (en) * 1998-12-24 2000-07-26 Rolls Royce Plc Gas turbine engine blade cooling air system
EP1013882A3 (en) * 1998-12-24 2001-12-05 Rolls-Royce Plc Gas turbine engine internal air system
US6357999B1 (en) 1998-12-24 2002-03-19 Rolls-Royce Plc Gas turbine engine internal air system
GB2345942B (en) * 1998-12-24 2002-08-07 Rolls Royce Plc Gas turbine engine internal air system
GB2366600A (en) * 2000-09-09 2002-03-13 Rolls Royce Plc Cooling arrangement for trailing edge of aerofoil

Also Published As

Publication number Publication date
NL164358C (en) 1980-12-15
NL7300634A (en) 1973-07-20
DE2202858C2 (en) 1974-02-28
BE794195A (en) 1973-07-18
DE2202858B1 (en) 1973-07-26
CH547431A (en) 1974-03-29
NL164358B (en) 1980-07-15
FR2168802A5 (en) 1973-08-31
IT978243B (en) 1974-09-20
SE381311B (en) 1975-12-01
US3807892A (en) 1974-04-30
JPS5145726B2 (en) 1976-12-04
CA967095A (en) 1975-05-06
JPS4882210A (en) 1973-11-02

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
732 Registration of transactions, instruments or events in the register (sect. 32/1977)
PE20 Patent expired after termination of 20 years

Effective date: 19930115