EP1048822A3 - Hitzeschild für eine Gasturbine - Google Patents

Hitzeschild für eine Gasturbine Download PDF

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Publication number
EP1048822A3
EP1048822A3 EP00810216A EP00810216A EP1048822A3 EP 1048822 A3 EP1048822 A3 EP 1048822A3 EP 00810216 A EP00810216 A EP 00810216A EP 00810216 A EP00810216 A EP 00810216A EP 1048822 A3 EP1048822 A3 EP 1048822A3
Authority
EP
European Patent Office
Prior art keywords
heat shield
gas turbine
shield segments
hot gas
cooling
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.)
Granted
Application number
EP00810216A
Other languages
English (en)
French (fr)
Other versions
EP1048822B1 (de
EP1048822A2 (de
Inventor
Christoph Nagler
Christof Pfeiffer
Ulrich Wellenkamp
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.)
GE Vernova GmbH
Original Assignee
Alstom SA
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 Alstom SA filed Critical Alstom SA
Publication of EP1048822A2 publication Critical patent/EP1048822A2/de
Publication of EP1048822A3 publication Critical patent/EP1048822A3/de
Application granted granted Critical
Publication of EP1048822B1 publication Critical patent/EP1048822B1/de
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
    • 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
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components

Landscapes

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

Abstract

Ein Hitzeschild für eine Gasturbine (10), welches die im Heissgaskanal (11) der Gasturbine (10) rotierenden Laufschaufeln (12) einer Stufe der Gasturbine (10) ringförmig umschliesst, besteht aus einer Mehrzahl von in Umfangsrichtung hintereinander angeordneten, kreissegmentförmig gekrümmten und von aussen gekühlten Hitzeschildsegmenten (17, 17'), deren Längsseiten als in Umfangsrichtung verlaufende, entsprechend gekrümmte Schienen mit jeweils einem Paar in axialer Richtung abstehender, parallel verlaufender und voneinander beabstandeter Arme (21, 22 bzw. 23, 24) ausgebildet sind. Die Hitzeschildsegmente (17, 17') sind unter Bildung eines mit Kühlluft beaufschlagbaren Hohlraumes (20) an der Innenseite eines ringförmigen Trägers (16) befestigt, welcher den Hitzeschild konzentrisch umgibt, derart, dass zwischen den Längsseiten der Hitzeschildsegmente (17, 17') und den angrenzenden Elementen (14, 15), welche den Heissgaskanal (11) nach aussen begrenzen, jeweils ein radialer Spalt (29, 30) gebildet wird
Bei einem solchen Hitzeschild wird eine verbesserte Kühlung dadurch erreicht, dass in beiden Längsseiten der Hitzeschildsegmente Kühlbohrungen (27, 28) vorgesehen sind, durch welche Kühlluft aus dem Hohlraum (20) in die zwischen den Armpaaren (21, 22 bzw. 23, 24) gebildeten Zwischenräume (25, 26) und von dort in die Spalte (29, 30) einströmen und dem Eindringen von Heissgasen aus dem Heissgaskanal (11) in die Spalte (29, 30) entgegenwirken kann.
EP00810216A 1999-04-29 2000-03-15 Hitzeschild für eine Gasturbine Expired - Lifetime EP1048822B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19919654 1999-04-29
DE19919654A DE19919654A1 (de) 1999-04-29 1999-04-29 Hitzeschild für eine Gasturbine

Publications (3)

Publication Number Publication Date
EP1048822A2 EP1048822A2 (de) 2000-11-02
EP1048822A3 true EP1048822A3 (de) 2002-07-31
EP1048822B1 EP1048822B1 (de) 2006-05-17

Family

ID=7906382

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810216A Expired - Lifetime EP1048822B1 (de) 1999-04-29 2000-03-15 Hitzeschild für eine Gasturbine

Country Status (3)

Country Link
US (1) US6302642B1 (de)
EP (1) EP1048822B1 (de)
DE (2) DE19919654A1 (de)

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19938443A1 (de) * 1999-08-13 2001-02-15 Abb Alstom Power Ch Ag Befestigungs- und Fixierungsvorrichtung
DE19945581B4 (de) * 1999-09-23 2014-04-03 Alstom Technology Ltd. Turbomaschine
WO2001066914A1 (en) * 2000-03-07 2001-09-13 Mitsubishi Heavy Industries, Ltd. Gas turbine split ring
JP4698847B2 (ja) * 2001-01-19 2011-06-08 三菱重工業株式会社 ガスタービン分割環
GB2378730B (en) * 2001-08-18 2005-03-16 Rolls Royce Plc Cooled segments surrounding turbine blades
US6783324B2 (en) * 2002-08-15 2004-08-31 General Electric Company Compressor bleed case
US6899518B2 (en) 2002-12-23 2005-05-31 Pratt & Whitney Canada Corp. Turbine shroud segment apparatus for reusing cooling air
JP4191552B2 (ja) * 2003-07-14 2008-12-03 三菱重工業株式会社 ガスタービン尾筒の冷却構造
US7165937B2 (en) * 2004-12-06 2007-01-23 General Electric Company Methods and apparatus for maintaining rotor assembly tip clearances
US7520715B2 (en) * 2005-07-19 2009-04-21 Pratt & Whitney Canada Corp. Turbine shroud segment transpiration cooling with individual cast inlet and outlet cavities
US20070020088A1 (en) * 2005-07-20 2007-01-25 Pratt & Whitney Canada Corp. Turbine shroud segment impingement cooling on vane outer shroud
US7278820B2 (en) * 2005-10-04 2007-10-09 Siemens Power Generation, Inc. Ring seal system with reduced cooling requirements
US7334985B2 (en) * 2005-10-11 2008-02-26 United Technologies Corporation Shroud with aero-effective cooling
US7740444B2 (en) * 2006-11-30 2010-06-22 General Electric Company Methods and system for cooling integral turbine shround assemblies
US7740442B2 (en) * 2006-11-30 2010-06-22 General Electric Company Methods and system for cooling integral turbine nozzle and shroud assemblies
US7722315B2 (en) * 2006-11-30 2010-05-25 General Electric Company Method and system to facilitate preferentially distributed recuperated film cooling of turbine shroud assembly
US7665953B2 (en) * 2006-11-30 2010-02-23 General Electric Company Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies
CA2684371C (en) * 2007-04-19 2014-10-21 Alstom Technology Ltd Stator heat shield
US8240980B1 (en) 2007-10-19 2012-08-14 Florida Turbine Technologies, Inc. Turbine inter-stage gap cooling and sealing arrangement
US8251637B2 (en) * 2008-05-16 2012-08-28 General Electric Company Systems and methods for modifying modal vibration associated with a turbine
US8128344B2 (en) * 2008-11-05 2012-03-06 General Electric Company Methods and apparatus involving shroud cooling
US8556575B2 (en) * 2010-03-26 2013-10-15 United Technologies Corporation Blade outer seal for a gas turbine engine
RU2543101C2 (ru) * 2010-11-29 2015-02-27 Альстом Текнолоджи Лтд Осевая газовая турбина
EP2508713A1 (de) * 2011-04-04 2012-10-10 Siemens Aktiengesellschaft Gasturbine mit einem Wärmeschild sowie Betriebsverfahren
US9574455B2 (en) * 2012-07-16 2017-02-21 United Technologies Corporation Blade outer air seal with cooling features
EP2949873A1 (de) * 2014-05-27 2015-12-02 Siemens Aktiengesellschaft Turbomaschine mit Aufnahmeschutz und Verwendung der Turbomaschine
WO2015191185A1 (en) 2014-06-12 2015-12-17 General Electric Company Shroud hanger assembly
FR3036436B1 (fr) 2015-05-22 2020-01-24 Safran Ceramics Ensemble d'anneau de turbine avec maintien par brides
US10221713B2 (en) * 2015-05-26 2019-03-05 Rolls-Royce Corporation Shroud cartridge having a ceramic matrix composite seal segment
ES2723400T3 (es) 2015-12-07 2019-08-27 MTU Aero Engines AG Estructura de carcasa de una turbomáquina con pantalla de protección térmica
US20170198602A1 (en) * 2016-01-11 2017-07-13 General Electric Company Gas turbine engine with a cooled nozzle segment
KR101965500B1 (ko) * 2017-09-11 2019-04-03 두산중공업 주식회사 터빈의 블레이드 시일 구조 및 이를 포함하는 터빈 및 가스터빈
FR3112806B1 (fr) * 2020-07-23 2022-10-21 Safran Aircraft Engines Couronne de maintien de secteurs d’étanchéité d’une turbine basse pression

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3583824A (en) * 1969-10-02 1971-06-08 Gen Electric Temperature controlled shroud and shroud support
US3864056A (en) * 1973-07-27 1975-02-04 Westinghouse Electric Corp Cooled turbine blade ring assembly
GB1484288A (en) * 1975-12-03 1977-09-01 Rolls Royce Gas turbine engines
US4222706A (en) * 1977-08-26 1980-09-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Porous abradable shroud with transverse partitions
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
US4642024A (en) * 1984-12-05 1987-02-10 United Technologies Corporation Coolable stator assembly for a rotary machine
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US5039562A (en) * 1988-10-20 1991-08-13 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

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
US4177004A (en) 1977-10-31 1979-12-04 General Electric Company Combined turbine shroud and vane support structure
JPS5857658B2 (ja) * 1980-04-02 1983-12-21 工業技術院長 セラミツクスによる高熱曝露壁面の熱遮断構造
US4526226A (en) * 1981-08-31 1985-07-02 General Electric Company Multiple-impingement cooled structure
US4551064A (en) 1982-03-05 1985-11-05 Rolls-Royce Limited Turbine shroud and turbine shroud assembly
US5071313A (en) 1990-01-16 1991-12-10 General Electric Company Rotor blade shroud segment
US5169287A (en) 1991-05-20 1992-12-08 General Electric Company Shroud cooling assembly for gas turbine engine
US5584651A (en) 1994-10-31 1996-12-17 General Electric Company Cooled shroud
US6126389A (en) * 1998-09-02 2000-10-03 General Electric Co. Impingement cooling for the shroud of a gas turbine
US6224329B1 (en) * 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3583824A (en) * 1969-10-02 1971-06-08 Gen Electric Temperature controlled shroud and shroud support
US3864056A (en) * 1973-07-27 1975-02-04 Westinghouse Electric Corp Cooled turbine blade ring assembly
GB1484288A (en) * 1975-12-03 1977-09-01 Rolls Royce Gas turbine engines
US4222706A (en) * 1977-08-26 1980-09-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Porous abradable shroud with transverse partitions
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US4642024A (en) * 1984-12-05 1987-02-10 United Technologies Corporation Coolable stator assembly for a rotary machine
US5039562A (en) * 1988-10-20 1991-08-13 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

Also Published As

Publication number Publication date
DE50012746D1 (de) 2006-06-22
EP1048822B1 (de) 2006-05-17
US6302642B1 (en) 2001-10-16
EP1048822A2 (de) 2000-11-02
DE19919654A1 (de) 2000-11-02

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