GB1435820A - Gas turbine combustion apparatus liner - Google Patents

Gas turbine combustion apparatus liner

Info

Publication number
GB1435820A
GB1435820A GB5903173A GB5903173A GB1435820A GB 1435820 A GB1435820 A GB 1435820A GB 5903173 A GB5903173 A GB 5903173A GB 5903173 A GB5903173 A GB 5903173A GB 1435820 A GB1435820 A GB 1435820A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
wall
zone
holes
dilution
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
GB5903173A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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 Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB1435820A publication Critical patent/GB1435820A/en
Expired legal-status Critical Current

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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1435820 Gas turbine combustion chamber GENERAL MOTORS CORP 20 Dec 1973 [6 April 1973] 59031/73 Heading F1L A gas turbine combustion chamber comprises an outer casing 3 to which compressed air is fed via an annular chamber 11 and a perforated baffle 12, and a liner 4 comprising in sequence from its upstream end a perforated dome 14 having a fuel inlet nozzle 20; a combustion zone 15 having primary air inlet holes 23 and defining cooling air entrances 18 between the dome and the corrugated end of the wall 15; a residence zone within an imperforate wall 16 for completion of combustion; and a dilution zone defined between the outer wall 16 having dilution holes 28, and a centre body 30 mounted on the wall 16 by hollow struts 36 through which air is fed to the body 30 for expulsion at its upstream end through holes 38, 39 behind baffles 35, 34 respectively. The dilution zone terminates adjacent the annular inlet 6 of the gas turbine.
GB5903173A 1973-04-06 1973-12-20 Gas turbine combustion apparatus liner Expired GB1435820A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00348682A US3851465A (en) 1973-04-06 1973-04-06 Annular dilution zone combustor

Publications (1)

Publication Number Publication Date
GB1435820A true GB1435820A (en) 1976-05-19

Family

ID=23369090

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5903173A Expired GB1435820A (en) 1973-04-06 1973-12-20 Gas turbine combustion apparatus liner

Country Status (3)

Country Link
US (1) US3851465A (en)
CA (1) CA982830A (en)
GB (1) GB1435820A (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4171612A (en) * 1972-12-11 1979-10-23 Zwick Eugene B Low emission burner construction
US4173118A (en) * 1974-08-27 1979-11-06 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus employing staged combustion
US4292810A (en) * 1979-02-01 1981-10-06 Westinghouse Electric Corp. Gas turbine combustion chamber
US4903492A (en) * 1988-09-07 1990-02-27 The United States Of America As Represented By The Secretary Of The Air Force Dilution air dispensing apparatus
US5220795A (en) * 1991-04-16 1993-06-22 General Electric Company Method and apparatus for injecting dilution air
US5277021A (en) * 1991-05-13 1994-01-11 Sundstrand Corporation Very high altitude turbine combustor
US5373694A (en) * 1992-11-17 1994-12-20 United Technologies Corporation Combustor seal and support
US7762074B2 (en) * 2006-04-04 2010-07-27 Siemens Energy, Inc. Air flow conditioner for a combustor can of a gas turbine engine
US8397511B2 (en) * 2009-05-19 2013-03-19 General Electric Company System and method for cooling a wall of a gas turbine combustor

Also Published As

Publication number Publication date
US3851465A (en) 1974-12-03
CA982830A (en) 1976-02-03

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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