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DE60017396D1 - Vorrichtung zur reduzierung der kühlung für einen turbineneinlasskanal - Google Patents

Vorrichtung zur reduzierung der kühlung für einen turbineneinlasskanal

Info

Publication number
DE60017396D1
DE60017396D1 DE60017396T DE60017396T DE60017396D1 DE 60017396 D1 DE60017396 D1 DE 60017396D1 DE 60017396 T DE60017396 T DE 60017396T DE 60017396 T DE60017396 T DE 60017396T DE 60017396 D1 DE60017396 D1 DE 60017396D1
Authority
DE
Germany
Prior art keywords
entry channel
reducing cooling
turbine entry
turbine
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.)
Expired - Lifetime
Application number
DE60017396T
Other languages
English (en)
Other versions
DE60017396T2 (de
Inventor
J Gates
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.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada 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 Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Application granted granted Critical
Publication of DE60017396D1 publication Critical patent/DE60017396D1/de
Publication of DE60017396T2 publication Critical patent/DE60017396T2/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
DE60017396T 1999-06-10 2000-06-07 Vorrichtung zur reduzierung der kühlung für einen turbineneinlasskanal Expired - Lifetime DE60017396T2 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US09/329,785 US6269628B1 (en) 1999-06-10 1999-06-10 Apparatus for reducing combustor exit duct cooling
US329785 1999-06-10
PCT/CA2000/000671 WO2000077348A1 (en) 1999-06-10 2000-06-07 Apparatus for reducing combustor exit duct cooling

Publications (2)

Publication Number Publication Date
DE60017396D1 true DE60017396D1 (de) 2005-02-17
DE60017396T2 DE60017396T2 (de) 2005-12-29

Family

ID=23287010

Family Applications (1)

Application Number Title Priority Date Filing Date
DE60017396T Expired - Lifetime DE60017396T2 (de) 1999-06-10 2000-06-07 Vorrichtung zur reduzierung der kühlung für einen turbineneinlasskanal

Country Status (6)

Country Link
US (1) US6269628B1 (de)
EP (1) EP1185765B1 (de)
JP (1) JP2003502546A (de)
CA (1) CA2374753C (de)
DE (1) DE60017396T2 (de)
WO (1) WO2000077348A1 (de)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10132002C5 (de) * 2001-07-03 2009-12-31 Windmöller & Hölscher Kg Direktangetriebener Extruder
US7000406B2 (en) * 2003-12-03 2006-02-21 Pratt & Whitney Canada Corp. Gas turbine combustor sliding joint
US7200987B2 (en) * 2004-06-18 2007-04-10 General Electric Company Off-axis pulse detonation configuration for gas turbine engine
US7350358B2 (en) * 2004-11-16 2008-04-01 Pratt & Whitney Canada Corp. Exit duct of annular reverse flow combustor and method of making the same
US7523602B2 (en) * 2005-09-27 2009-04-28 United Technologies Corporation Turbine exhaust catalyst
US7934382B2 (en) * 2005-12-22 2011-05-03 United Technologies Corporation Combustor turbine interface
US7836702B2 (en) * 2006-09-15 2010-11-23 Pratt & Whitney Canada Corp. Gas turbine combustor exit duct and HP vane interface
US8794005B2 (en) * 2006-12-21 2014-08-05 Pratt & Whitney Canada Corp. Combustor construction
US7665310B2 (en) * 2006-12-27 2010-02-23 General Electric Company Gas turbine engine having a cooling-air nacelle-cowl duct integral with a nacelle cowl
EP2483529B1 (de) * 2009-09-28 2013-08-28 Siemens Aktiengesellschaft Gasturbinendüsenanordnung und gasturbine
US8864492B2 (en) * 2011-06-23 2014-10-21 United Technologies Corporation Reverse flow combustor duct attachment
US9388739B2 (en) 2012-05-02 2016-07-12 Pratt & Whitney Canada Corp. Air cooler system for gas turbine engines
US20140174098A1 (en) * 2012-12-20 2014-06-26 United Technologies Corporation Turbine disc with reduced neck stress concentration
WO2014159200A1 (en) 2013-03-14 2014-10-02 United Technologies Corporation Gas turbine engine turbine impeller pressurization
US20140366544A1 (en) * 2013-06-13 2014-12-18 Pratt & Whitney Canada Corp. Combustor exit duct for gas turbine engines
EP2915957A1 (de) * 2014-03-05 2015-09-09 Siemens Aktiengesellschaft Gegossene rohrförmige Leitung für eine Gasturbine und Herstellungsverfahren dafür
US10337736B2 (en) * 2015-07-24 2019-07-02 Pratt & Whitney Canada Corp. Gas turbine engine combustor and method of forming same
US10928069B2 (en) * 2016-06-17 2021-02-23 Pratt & Whitney Canada Corp. Small exit duct for a reverse flow combustor with integrated fastening elements
US10527288B2 (en) * 2016-06-17 2020-01-07 Pratt & Whitney Canada Corp. Small exit duct for a reverse flow combustor with integrated cooling elements
US10393381B2 (en) * 2017-01-27 2019-08-27 General Electric Company Unitary flow path structure
US11402100B2 (en) * 2018-11-15 2022-08-02 Pratt & Whitney Canada Corp. Ring assembly for double-skin combustor liner
JP7252791B2 (ja) * 2019-03-07 2023-04-05 本田技研工業株式会社 ガスタービンエンジン
FR3097299B1 (fr) * 2019-06-13 2021-07-23 Safran Ensemble pour une turbine a gaz
US11624323B2 (en) 2020-08-13 2023-04-11 Unison Industries, Llc Air turbine starter with primary and secondary air flow paths
US12486774B2 (en) 2023-12-22 2025-12-02 Rtx Corporation Cooling nozzle vanes of a turbine engine
US12215604B1 (en) * 2023-12-22 2025-02-04 Rtx Corporation Cooling nozzle vanes of a turbine engine

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3652181A (en) 1970-11-23 1972-03-28 Carl F Wilhelm Jr Cooling sleeve for gas turbine combustor transition member
US3671171A (en) * 1970-11-27 1972-06-20 Avco Corp Annular combustors
US3691766A (en) * 1970-12-16 1972-09-19 Rolls Royce Combustion chambers
US3761205A (en) 1972-03-20 1973-09-25 Avco Corp Easily maintainable gas turbine engine
US3914070A (en) 1973-11-19 1975-10-21 Avco Corp Two-stage tie-down of turbomachine rotor
US4195476A (en) * 1978-04-27 1980-04-01 General Motors Corporation Combustor construction
CH633347A5 (de) * 1978-08-03 1982-11-30 Bbc Brown Boveri & Cie Gasturbine.
DE2907748C2 (de) * 1979-02-28 1987-02-12 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur Minimierung und Konstanthaltung des Schaufelspitzenspiels einer axial durchströmten Hochdruckturbine eines Gasturbinentriebwerks
US4639188A (en) 1984-12-04 1987-01-27 Sundstrand Corporation Turbine wheel containment
DE3514352A1 (de) * 1985-04-20 1986-10-23 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gasturbinentriebwerk mit einrichtungen zur abzweigung von verdichterluft zur kuehlung von heissteilen
US4955192A (en) 1988-12-12 1990-09-11 Sundstrand Corporation Containment ring for radial inflow turbine
JPH0299238U (de) * 1989-01-26 1990-08-07
JPH02105548U (de) * 1989-02-10 1990-08-22
JPH02110237U (de) * 1989-02-21 1990-09-04
JPH02110203U (de) * 1989-02-21 1990-09-04
US5280703A (en) 1989-12-11 1994-01-25 Sundstrand Corporation Turbine nozzle cooling
US5271220A (en) 1992-10-16 1993-12-21 Sundstrand Corporation Combustor heat shield for a turbine containment ring
GB9304994D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Improvements in or relating to gas turbine engines
US5387081A (en) 1993-12-09 1995-02-07 Pratt & Whitney Canada, Inc. Compressor diffuser
JPH0835401A (ja) * 1994-07-26 1996-02-06 Yanmar Diesel Engine Co Ltd ガスタービンの静翼取付機構
US5758504A (en) * 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner

Also Published As

Publication number Publication date
CA2374753A1 (en) 2000-12-21
JP2003502546A (ja) 2003-01-21
EP1185765A1 (de) 2002-03-13
DE60017396T2 (de) 2005-12-29
US6269628B1 (en) 2001-08-07
WO2000077348A1 (en) 2000-12-21
EP1185765B1 (de) 2005-01-12
CA2374753C (en) 2011-01-18

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition