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GB1311630A - Gas turbine power plant - Google Patents

Gas turbine power plant

Info

Publication number
GB1311630A
GB1311630A GB3910871A GB3910871A GB1311630A GB 1311630 A GB1311630 A GB 1311630A GB 3910871 A GB3910871 A GB 3910871A GB 3910871 A GB3910871 A GB 3910871A GB 1311630 A GB1311630 A GB 1311630A
Authority
GB
United Kingdom
Prior art keywords
transition member
wall
turbine
sleeve
cooling fluid
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
GB3910871A
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
Publication of GB1311630A publication Critical patent/GB1311630A/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
    • 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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Landscapes

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

Abstract

1311630 Gas-turbine combustion chambers GENERAL ELECTRIC CO 20 Aug 1971 [23 Nov 1970] 39108/71 Heading F1L A transition member conducting hot combustion gases from a combustion chamber to a gas turbine inlet passage and disposed in a chamber connected to a source of pressurized cooling fluid is surrounded by a sleeve member, the radially outer wall of the transition member being perforated to admit jets of cooling fluid for impingement cooling of the radially outer wall of the transition member, and the radially inner wall of the transition member having openings to admit cooling fluid from the sleeve into the transition member for improving the radial temperature gradient of the hot combustion gases entering the turbine. The transition member 6, which is shaped in cross-section to connect the circular outlet end of a flame tube to an arc of radially extending turbine nozzle blades, is surrounded at its outlet end by a sleeve 11 having a flanged periphery 12 attached, as by spot welding, to the transition member. Air from the compressor of the engine can pass through a large number of small perforations 18 to provide impingement cooling of the radially outer wall 14 of the transition member 6. This air passes through the space 13 to enter the transition member 6 via a small number of large holes 19 in the radially inner wall 15 of the transition member to cool the combustion gases in the radially inner part of the gas path where the turbine rotor blade stresses are highest.
GB3910871A 1970-11-23 1971-08-20 Gas turbine power plant Expired GB1311630A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US9165970A 1970-11-23 1970-11-23

Publications (1)

Publication Number Publication Date
GB1311630A true GB1311630A (en) 1973-03-28

Family

ID=22228970

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3910871A Expired GB1311630A (en) 1970-11-23 1971-08-20 Gas turbine power plant

Country Status (8)

Country Link
US (1) US3652181A (en)
JP (1) JPS5411443B1 (en)
CH (1) CH538602A (en)
DE (1) DE2155107A1 (en)
FR (1) FR2115343B1 (en)
GB (1) GB1311630A (en)
IT (1) IT941241B (en)
NL (1) NL7112400A (en)

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3844116A (en) * 1972-09-06 1974-10-29 Avco Corp Duct wall and reverse flow combustor incorporating same
DE2728399C2 (en) * 1977-06-24 1982-04-22 Brown, Boveri & Cie Ag, 6800 Mannheim Combustion chamber for a gas turbine
US4195474A (en) * 1977-10-17 1980-04-01 General Electric Company Liquid-cooled transition member to turbine inlet
SE426982B (en) * 1980-03-19 1983-02-21 Fagersta Ab SET AND DEVICE FOR RECOVERY OF HEAT FROM COGAS GAS
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
CA1263243A (en) * 1985-05-14 1989-11-28 Lewis Berkley Davis, Jr. Impingement cooled transition duct
JPH0752014B2 (en) * 1986-03-20 1995-06-05 株式会社日立製作所 Gas turbine combustor
CA1309873C (en) * 1987-04-01 1992-11-10 Graham P. Butt Gas turbine combustor transition duct forced convection cooling
US5394687A (en) * 1993-12-03 1995-03-07 The United States Of America As Represented By The Department Of Energy Gas turbine vane cooling system
US6018950A (en) * 1997-06-13 2000-02-01 Siemens Westinghouse Power Corporation Combustion turbine modular cooling panel
US6269628B1 (en) * 1999-06-10 2001-08-07 Pratt & Whitney Canada Corp. Apparatus for reducing combustor exit duct cooling
US6334310B1 (en) * 2000-06-02 2002-01-01 General Electric Company Fracture resistant support structure for a hula seal in a turbine combustor and related method
JP2002243154A (en) * 2001-02-16 2002-08-28 Mitsubishi Heavy Ind Ltd Gas turbine combustor and tail cylinder outlet structure thereof
DE50107283D1 (en) 2001-06-18 2005-10-06 Siemens Ag Gas turbine with a compressor for air
JP4191552B2 (en) * 2003-07-14 2008-12-03 三菱重工業株式会社 Cooling structure of gas turbine tail tube
US7574865B2 (en) * 2004-11-18 2009-08-18 Siemens Energy, Inc. Combustor flow sleeve with optimized cooling and airflow distribution
US7870739B2 (en) * 2006-02-02 2011-01-18 Siemens Energy, Inc. Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions
US7827801B2 (en) * 2006-02-09 2010-11-09 Siemens Energy, Inc. Gas turbine engine transitions comprising closed cooled transition cooling channels
US7886517B2 (en) * 2007-05-09 2011-02-15 Siemens Energy, Inc. Impingement jets coupled to cooling channels for transition cooling
EP2028344A1 (en) * 2007-08-21 2009-02-25 Siemens Aktiengesellschaft Transition duct
WO2009103671A1 (en) * 2008-02-20 2009-08-27 Alstom Technology Ltd Gas turbine having an improved cooling architecture
US20100005804A1 (en) * 2008-07-11 2010-01-14 General Electric Company Combustor structure
US20100037622A1 (en) * 2008-08-18 2010-02-18 General Electric Company Contoured Impingement Sleeve Holes
US8033119B2 (en) * 2008-09-25 2011-10-11 Siemens Energy, Inc. Gas turbine transition duct
US8448416B2 (en) * 2009-03-30 2013-05-28 General Electric Company Combustor liner
US8695322B2 (en) * 2009-03-30 2014-04-15 General Electric Company Thermally decoupled can-annular transition piece
US8647053B2 (en) 2010-08-09 2014-02-11 Siemens Energy, Inc. Cooling arrangement for a turbine component
JP5579011B2 (en) * 2010-10-05 2014-08-27 株式会社日立製作所 Gas turbine combustor
US20120324898A1 (en) * 2011-06-21 2012-12-27 Mcmahan Kevin Weston Combustor assembly for use in a turbine engine and methods of assembling same
US9133722B2 (en) * 2012-04-30 2015-09-15 General Electric Company Transition duct with late injection in turbine system

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479573A (en) * 1943-10-20 1949-08-23 Gen Electric Gas turbine power plant
CH304143A (en) * 1950-05-09 1954-12-31 Maschf Augsburg Nuernberg Ag Method for operating a gas turbine plant and device for carrying out the method.
US2958194A (en) * 1951-09-24 1960-11-01 Power Jets Res & Dev Ltd Cooled flame tube
US3135496A (en) * 1962-03-02 1964-06-02 Gen Electric Axial flow turbine with radial temperature gradient
US3433015A (en) * 1965-06-23 1969-03-18 Nasa Gas turbine combustion apparatus
US3490747A (en) * 1967-11-29 1970-01-20 Westinghouse Electric Corp Temperature profiling means for turbine inlet
GB1180706A (en) * 1968-08-02 1970-02-11 Rolls Royce Flame Tube

Also Published As

Publication number Publication date
CH538602A (en) 1973-06-30
FR2115343B1 (en) 1974-05-31
FR2115343A1 (en) 1972-07-07
IT941241B (en) 1973-03-01
NL7112400A (en) 1972-05-25
DE2155107A1 (en) 1972-05-25
US3652181A (en) 1972-03-28
JPS5411443B1 (en) 1979-05-15

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee