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TW368554B - Gas turbine regenerative cooled combustor - Google Patents

Gas turbine regenerative cooled combustor

Info

Publication number
TW368554B
TW368554B TW085111897A TW85111897A TW368554B TW 368554 B TW368554 B TW 368554B TW 085111897 A TW085111897 A TW 085111897A TW 85111897 A TW85111897 A TW 85111897A TW 368554 B TW368554 B TW 368554B
Authority
TW
Taiwan
Prior art keywords
cooling fluid
cooling
compressed air
manifold
combustor
Prior art date
Application number
TW085111897A
Other languages
Chinese (zh)
Inventor
Gerard Mcquiggan
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
Application granted granted Critical
Publication of TW368554B publication Critical patent/TW368554B/en

Links

Classifications

    • 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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F02C7/22—Fuel supply systems
    • F02C7/224—Heating fuel before feeding to the burner

Landscapes

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

Abstract

A combustor having a wall within and around which a plurality of cooling passages are arranged. A supply pipe brings a cooling fluid, such as gaseous fuel or compressed air, to a manifold that encircles the inlets of each of the holes. The manifold divides the cooling fluid in a number of small streams that flow axially toward a circumferentially extending array of outlets, thereby heating the fluid and cooling the combustor wall. In an embodiment in which the cooling fluid is compressed air, the passages discharge the heated compressed air to a chamber from which it enters the inlets of the combusts. In an embodiment in which the cooling fluid is gaseous fuel, a second manifold that encircles the outlets collects the fuel and then directs it to a fuel nozzle for introduction into the combustion zone.
TW085111897A 1995-10-17 1996-09-30 Gas turbine regenerative cooled combustor TW368554B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US54434995A 1995-10-17 1995-10-17

Publications (1)

Publication Number Publication Date
TW368554B true TW368554B (en) 1999-09-01

Family

ID=24171816

Family Applications (1)

Application Number Title Priority Date Filing Date
TW085111897A TW368554B (en) 1995-10-17 1996-09-30 Gas turbine regenerative cooled combustor

Country Status (2)

Country Link
TW (1) TW368554B (en)
WO (1) WO1997014875A1 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3110338B2 (en) * 1997-02-12 2000-11-20 東北電力株式会社 Combustor cooling structure with steam
US5906093A (en) * 1997-02-21 1999-05-25 Siemens Westinghouse Power Corporation Gas turbine combustor transition
JP3310900B2 (en) 1997-04-15 2002-08-05 三菱重工業株式会社 Cooling structure of combustor transition piece
CA2288557C (en) * 1998-11-12 2007-02-06 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor cooling structure
JP2002243154A (en) * 2001-02-16 2002-08-28 Mitsubishi Heavy Ind Ltd Gas turbine combustor and tail cylinder outlet structure thereof
JP3831638B2 (en) 2001-08-09 2006-10-11 三菱重工業株式会社 Plate-like body joining method, joined body, tail tube for gas turbine combustor, and gas turbine combustor
EP1400751A1 (en) 2002-09-17 2004-03-24 Siemens Aktiengesellschaft Combustion chamber for a gas turbine
EP2199681A1 (en) 2008-12-18 2010-06-23 Siemens Aktiengesellschaft Gas turbine combustion chamber and gas turbine
EP2270397A1 (en) 2009-06-09 2011-01-05 Siemens Aktiengesellschaft Gas turbine combustor and gas turbine
EP2261565A1 (en) 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Gas turbine reactor and gas turbines
GB201501971D0 (en) 2015-02-06 2015-03-25 Rolls Royce Plc A combustion chamber
GB201613208D0 (en) 2016-08-01 2016-09-14 Rolls Royce Plc A combustion chamber assembly and a combustion chamber segment
DE102021110614A1 (en) 2021-04-26 2022-10-27 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly for an engine with at least one heat exchange channel for fuel to be injected
EP4538515A1 (en) * 2023-10-12 2025-04-16 Airbus Operations (S.A.S.) Propulsion assembly for an aircraft comprising a system for heat exchange in the exhaust nozzle

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB618846A (en) * 1946-11-16 1949-02-28 Power Jets Res & Dev Ltd Improvements in or relating to fuel systems of gas turbines
US2716330A (en) * 1950-06-24 1955-08-30 Westinghouse Electric Corp Combustion apparatus having primary air preheating ducts
US3099909A (en) * 1959-05-21 1963-08-06 United Aircraft Corp Nozzle construction
DE2356572C3 (en) * 1973-11-13 1979-03-29 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Liquid-cooled rocket combustion chamber with thrust nozzle
GB2119447A (en) * 1982-05-01 1983-11-16 Kershaw H A Vapourising systems in jet propulsion or gas turbine engines
DE19505357C1 (en) * 1995-02-17 1996-05-23 Daimler Benz Aerospace Ag Aero engine or rocket wall cooling method

Also Published As

Publication number Publication date
WO1997014875A1 (en) 1997-04-24

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