GB2013788A - Gas turbine engine combustion equipment - Google Patents

Gas turbine engine combustion equipment

Info

Publication number
GB2013788A
GB2013788A GB7902578A GB7902578A GB2013788A GB 2013788 A GB2013788 A GB 2013788A GB 7902578 A GB7902578 A GB 7902578A GB 7902578 A GB7902578 A GB 7902578A GB 2013788 A GB2013788 A GB 2013788A
Authority
GB
United Kingdom
Prior art keywords
outlets
chamber
section
mixing section
gas turbine
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
GB7902578A
Other versions
GB2013788B (en
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB7902578A priority Critical patent/GB2013788B/en
Publication of GB2013788A publication Critical patent/GB2013788A/en
Application granted granted Critical
Publication of GB2013788B publication Critical patent/GB2013788B/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Abstract

A gas turbine engine comprises an annular combustion chamber (13) intended for low nitrogen oxide emission. The chamber has a premixing section (15, 16) in which an air-fuel mixture is formed before issuing through an annular array of outlets (22) at the end of the mixing section into a main section (21) of the chamber. Pilot combustion sections (18, 19) at opposite sides of the mixing section have outlets (28, 29) through which burning mixture from the pilot sections is discharged into main section (21). The array of outlets (22) defines openings (35) through which air/ fuel mixture from the mixing section (15, 16) is discharged across the outlets (28, 29) of the pilot sections (18, 19) to mix with and become ignited by the burning mixture. The mixing section comprises an annular duct (33) having walls (15, 16) which extend in the direction of the axis of the chamber and are straight in that direction though slightly convergent. <IMAGE>
GB7902578A 1978-01-28 1979-01-24 Gas turbine engine Expired GB2013788B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7902578A GB2013788B (en) 1978-01-28 1979-01-24 Gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB354878 1978-01-28
GB7902578A GB2013788B (en) 1978-01-28 1979-01-24 Gas turbine engine

Publications (2)

Publication Number Publication Date
GB2013788A true GB2013788A (en) 1979-08-15
GB2013788B GB2013788B (en) 1982-06-03

Family

ID=26238408

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7902578A Expired GB2013788B (en) 1978-01-28 1979-01-24 Gas turbine engine

Country Status (1)

Country Link
GB (1) GB2013788B (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276397A1 (en) * 1986-12-09 1988-08-03 BBC Brown Boveri AG Gas turbine combustor
EP0333307A1 (en) * 1988-01-08 1989-09-20 Hitachi, Ltd. Gas turbine combustor
EP0399336A1 (en) * 1989-05-24 1990-11-28 Hitachi, Ltd. Combustor and method of operating same
FR2660736A1 (en) * 1990-04-04 1991-10-11 Gen Electric POOR STAGE COMBUSTION ASSEMBLY.
FR2691235A1 (en) * 1992-05-13 1993-11-19 Snecma Combustion chamber comprising a gas separator assembly.
FR2694624A1 (en) * 1992-08-05 1994-02-11 Snecma Combustion chamber with several fuel injectors.
GB2292793A (en) * 1994-09-02 1996-03-06 Europ Gas Turbines Ltd Turbine combustion chamber
EP1924762A2 (en) * 2005-09-13 2008-05-28 Rolls-Royce Canada Limited Gas turbine engine combustion systems

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4805411A (en) * 1986-12-09 1989-02-21 Bbc Brown Boveri Ag Combustion chamber for gas turbine
CH672366A5 (en) * 1986-12-09 1989-11-15 Bbc Brown Boveri & Cie
EP0276397A1 (en) * 1986-12-09 1988-08-03 BBC Brown Boveri AG Gas turbine combustor
EP0333307A1 (en) * 1988-01-08 1989-09-20 Hitachi, Ltd. Gas turbine combustor
EP0399336A1 (en) * 1989-05-24 1990-11-28 Hitachi, Ltd. Combustor and method of operating same
US5201181A (en) * 1989-05-24 1993-04-13 Hitachi, Ltd. Combustor and method of operating same
FR2660736A1 (en) * 1990-04-04 1991-10-11 Gen Electric POOR STAGE COMBUSTION ASSEMBLY.
US5311743A (en) * 1992-05-13 1994-05-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas separator for a combustion chamber
FR2691235A1 (en) * 1992-05-13 1993-11-19 Snecma Combustion chamber comprising a gas separator assembly.
FR2694624A1 (en) * 1992-08-05 1994-02-11 Snecma Combustion chamber with several fuel injectors.
US5331814A (en) * 1992-08-05 1994-07-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Gas turbine combustion chamber with multiple fuel injector arrays
GB2292793A (en) * 1994-09-02 1996-03-06 Europ Gas Turbines Ltd Turbine combustion chamber
GB2292793B (en) * 1994-09-02 1998-06-24 Europ Gas Turbines Ltd Combustion chamber
EP1924762A2 (en) * 2005-09-13 2008-05-28 Rolls-Royce Canada Limited Gas turbine engine combustion systems
EP1924762A4 (en) * 2005-09-13 2009-10-28 Rolls Royce Canada Ltd Gas turbine engine combustion systems
US7841181B2 (en) 2005-09-13 2010-11-30 Rolls-Royce Power Engineering Plc Gas turbine engine combustion systems

Also Published As

Publication number Publication date
GB2013788B (en) 1982-06-03

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee