MX169327B - Mejoras en alabe de turbina con enfriamiento - Google Patents

Mejoras en alabe de turbina con enfriamiento

Info

Publication number
MX169327B
MX169327B MX019491A MX1949190A MX169327B MX 169327 B MX169327 B MX 169327B MX 019491 A MX019491 A MX 019491A MX 1949190 A MX1949190 A MX 1949190A MX 169327 B MX169327 B MX 169327B
Authority
MX
Mexico
Prior art keywords
fluid communication
channel
aerodynamic plane
air
outlet
Prior art date
Application number
MX019491A
Other languages
English (en)
Inventor
William Edward North
David Taylor Entenmann
John Paul Donlan
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
Publication of MX169327B publication Critical patent/MX169327B/es

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La presente invención se refiere a mejoras en álabe de turbina con enfriamiento para emplearlo en una turbina de gas de etapas múltiples, que tenga hileras de álabes enfriados por aire que se extienden en sentido radial desde cubiertas de sello en la trayectoria de los gases que fluyen en sentido general axial por la turbina; el álabe tiene un cuerpo hueco de plano aerodinámico con orificios que proveen a la comunicación de fluido con una fuente de aire para enfriamiento; entre el interior hueco y la trayectoria del flujo de gas, una cubierta externa con una entrada de aire enfriante hacia el interior hueco del cuerpo en plano aerodinámico que provee comunicación de fluido con una fuente de aire para enfriamiento; y que la entrada en la cubierta externa y la salida en la cubierta interna están alineadas con el primer canal, una cubierta interna con una salida de aire del interior del cuerpo del plano aerodinámico provee comunicación de fluido con una cubierta de sello a fin de permitir que una parte del aire circule desde el álabe por los orificios directamente a la trayectoria para gas y que otra parte del aire circule por la salida en la cubierta interna, caracterizadas porque el cuerpo del plano aerodinámico tiene en su interior un canal de pasos múltiples para el aire de enfriamiento que incluye un primer canal que se extiende a lo largo de las superficies de ataque del cuerpo de plano aerodinámico desde la entrada en la cubierta externa hasta un codo de retorno definido por el cuerpo de plano aerodinámico y la cubierta interna y un canal subsecuente en comunicación de fluido con el primer canal que se extiende a lo largo de las superficies de salida del cuerpo de plano aerodinámico en comunicación de fluido con el primer canal que se extiende a lo largo de las superficies de salida del cuerpo de plano aerodinámico en comunicación de fluido con los orificios.
MX019491A 1989-02-15 1990-02-14 Mejoras en alabe de turbina con enfriamiento MX169327B (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/310,554 US4930980A (en) 1989-02-15 1989-02-15 Cooled turbine vane

Publications (1)

Publication Number Publication Date
MX169327B true MX169327B (es) 1993-06-29

Family

ID=23203043

Family Applications (1)

Application Number Title Priority Date Filing Date
MX019491A MX169327B (es) 1989-02-15 1990-02-14 Mejoras en alabe de turbina con enfriamiento

Country Status (7)

Country Link
US (1) US4930980A (es)
EP (1) EP0383046A1 (es)
JP (1) JP2580356B2 (es)
KR (1) KR900013185A (es)
AU (1) AU623213B2 (es)
CA (1) CA2010061A1 (es)
MX (1) MX169327B (es)

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Publication number Priority date Publication date Assignee Title
US5207556A (en) * 1992-04-27 1993-05-04 General Electric Company Airfoil having multi-passage baffle
US5429478A (en) * 1994-03-31 1995-07-04 United Technologies Corporation Airfoil having a seal and an integral heat shield
US5498126A (en) * 1994-04-28 1996-03-12 United Technologies Corporation Airfoil with dual source cooling
US5511937A (en) * 1994-09-30 1996-04-30 Westinghouse Electric Corporation Gas turbine airfoil with a cooling air regulating seal
US5488825A (en) * 1994-10-31 1996-02-06 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
GB2294732A (en) * 1994-11-05 1996-05-08 Rolls Royce Plc Integral disc seal for turbomachine
EP0875665A3 (en) * 1994-11-10 1999-02-24 Westinghouse Electric Corporation Gas turbine vane with a cooled inner shroud
US5645397A (en) * 1995-10-10 1997-07-08 United Technologies Corporation Turbine vane assembly with multiple passage cooled vanes
US5752801A (en) * 1997-02-20 1998-05-19 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil and method of making same
JP3416447B2 (ja) * 1997-03-11 2003-06-16 三菱重工業株式会社 ガスタービンの翼冷却空気供給システム
US5813827A (en) * 1997-04-15 1998-09-29 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil
WO1998058158A1 (fr) * 1997-06-19 1998-12-23 Mitsubishi Heavy Industries, Ltd. Dispositif d'etancheite pour aubes de stator de turbine a gaz
US6146091A (en) * 1998-03-03 2000-11-14 Mitsubishi Heavy Industries, Ltd. Gas turbine cooling structure
US6474947B1 (en) 1998-03-13 2002-11-05 Mitsubishi Heavy Industries, Ltd. Film cooling hole construction in gas turbine moving-vanes
WO2001020133A1 (fr) * 1999-09-16 2001-03-22 Mitsubishi Heavy Industries, Ltd. Configuration a trous de refroidissement pour pellicule d'air dans les aubes mobiles d'une turbine a gaz
US6270317B1 (en) * 1999-12-18 2001-08-07 General Electric Company Turbine nozzle with sloped film cooling
US6508620B2 (en) * 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
RU2302534C2 (ru) 2001-12-11 2007-07-10 Альстом (Свитзерлэнд) Лтд. Газотурбинное устройство
US7118326B2 (en) * 2004-06-17 2006-10-10 Siemens Power Generation, Inc. Cooled gas turbine vane
JP4412081B2 (ja) * 2004-07-07 2010-02-10 株式会社日立製作所 ガスタービンとガスタービンの冷却方法
US7150601B2 (en) * 2004-12-23 2006-12-19 United Technologies Corporation Turbine airfoil cooling passageway
US20070009358A1 (en) * 2005-05-31 2007-01-11 Atul Kohli Cooled airfoil with reduced internal turn losses
US7549844B2 (en) * 2006-08-24 2009-06-23 Siemens Energy, Inc. Turbine airfoil cooling system with bifurcated and recessed trailing edge exhaust channels
JP5490091B2 (ja) * 2008-03-28 2014-05-14 アルストム テクノロジー リミテッド ガスタービン用案内翼
US8079813B2 (en) * 2009-01-19 2011-12-20 Siemens Energy, Inc. Turbine blade with multiple trailing edge cooling slots
US8328518B2 (en) * 2009-08-13 2012-12-11 Siemens Energy, Inc. Turbine vane for a gas turbine engine having serpentine cooling channels
EP2383435A1 (en) * 2010-04-29 2011-11-02 Siemens Aktiengesellschaft Turbine vane hollow inner rail
US9670797B2 (en) 2012-09-28 2017-06-06 United Technologies Corporation Modulated turbine vane cooling
US9359902B2 (en) 2013-06-28 2016-06-07 Siemens Energy, Inc. Turbine airfoil with ambient cooling system
US9957815B2 (en) * 2015-03-05 2018-05-01 United Technologies Corporation Gas powered turbine component including serpentine cooling
US10125632B2 (en) 2015-10-20 2018-11-13 General Electric Company Wheel space purge flow mixing chamber
US10132195B2 (en) 2015-10-20 2018-11-20 General Electric Company Wheel space purge flow mixing chamber
CA2954785A1 (en) 2016-01-25 2017-07-25 Rolls-Royce Corporation Forward flowing serpentine vane
KR102207971B1 (ko) 2019-06-21 2021-01-26 두산중공업 주식회사 터빈 베인, 및 이를 포함하는 터빈

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB938247A (en) * 1962-03-26 1963-10-02 Rolls Royce Gas turbine engine having cooled turbine blading
US3369792A (en) * 1966-04-07 1968-02-20 Gen Electric Airfoil vane
GB1355558A (en) * 1971-07-02 1974-06-05 Rolls Royce Cooled vane or blade for a gas turbine engine
US3945758A (en) * 1974-02-28 1976-03-23 Westinghouse Electric Corporation Cooling system for a gas turbine
US4416585A (en) * 1980-01-17 1983-11-22 Pratt & Whitney Aircraft Of Canada Limited Blade cooling for gas turbine engine
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
GB2163219B (en) * 1981-10-31 1986-08-13 Rolls Royce Cooled turbine blade
US4666368A (en) * 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines

Also Published As

Publication number Publication date
US4930980A (en) 1990-06-05
CA2010061A1 (en) 1990-08-15
JP2580356B2 (ja) 1997-02-12
EP0383046A1 (en) 1990-08-22
AU4877890A (en) 1990-08-23
KR900013185A (ko) 1990-09-03
JPH02233802A (ja) 1990-09-17
AU623213B2 (en) 1992-05-07

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