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GB1278590A - Combustion chambers for gas turbine engines - Google Patents

Combustion chambers for gas turbine engines

Info

Publication number
GB1278590A
GB1278590A GB44805/68A GB4480568A GB1278590A GB 1278590 A GB1278590 A GB 1278590A GB 44805/68 A GB44805/68 A GB 44805/68A GB 4480568 A GB4480568 A GB 4480568A GB 1278590 A GB1278590 A GB 1278590A
Authority
GB
United Kingdom
Prior art keywords
air
openings
air inlet
flow
inlets
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
GB44805/68A
Inventor
Alan Joseph Gerrard
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries Ltd
Joseph Lucas Industries Ltd
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 Lucas Industries Ltd, Joseph Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to GB44805/68A priority Critical patent/GB1278590A/en
Priority to US858770A priority patent/US3593518A/en
Priority to SE12892/69A priority patent/SE357028B/xx
Priority to DE19691947762 priority patent/DE1947762C3/en
Priority to FR6932136A priority patent/FR2018565A1/fr
Publication of GB1278590A publication Critical patent/GB1278590A/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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow

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

1278590 Gas turbine engine combustion equipment JOSEPH LUCAS (INDUSTRIES) Ltd 11 Sept 1969 [20 Sept 1968] 44805/68 Heading F1L A combustion chamber for a gas turbine engine comprises a primary air inlet duct, secondary air inlet nozzles and dilution air inlet nozzles, each air inlet incorporating a fluidic air-flow control device arranged so that the proportions of the total air-flow through the respective inlets may be controlled without varying the total resistance of the combustion chamber to air-flow therethrough. The combustion equipment shown comprises an annular flame tube 10, 11 having a primary air inlet 12 with a swirl device 13, secondary air inlets 15 defined by flanged openings in the walls 10, 11, and dilution air inlets 18 also defined by flanged openings in the walls 10, 11. The outer wall of the primary air inlet is formed with openings 14, see Fig.2, through which jets of air under pressure may be blown so as effectively to reduce the flow area of the duct. Alternatively suction may be applied to the openings 14 so as effectively to increase the flow area. The upstream sides of the flange portions defining the secondary and dilution air inlets 15, 18 are likewise formed with openings through which air under pressure may be blown or suction applied so as to vary the effective flow areas. Ring members 16 are disposed adjacent the flanged openings 15, 18 so as to define chambers 17, 19 by which the fluidic control is applied. The fluidic control jets may discharge tangentially of the air inlets.
GB44805/68A 1968-09-20 1968-09-20 Combustion chambers for gas turbine engines Expired GB1278590A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
GB44805/68A GB1278590A (en) 1968-09-20 1968-09-20 Combustion chambers for gas turbine engines
US858770A US3593518A (en) 1968-09-20 1969-09-17 Combustion chambers for gas turbine engines
SE12892/69A SE357028B (en) 1968-09-20 1969-09-19
DE19691947762 DE1947762C3 (en) 1968-09-20 1969-09-20 Flame tube for gas turbines
FR6932136A FR2018565A1 (en) 1968-09-20 1969-09-22

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB44805/68A GB1278590A (en) 1968-09-20 1968-09-20 Combustion chambers for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1278590A true GB1278590A (en) 1972-06-21

Family

ID=10434833

Family Applications (1)

Application Number Title Priority Date Filing Date
GB44805/68A Expired GB1278590A (en) 1968-09-20 1968-09-20 Combustion chambers for gas turbine engines

Country Status (4)

Country Link
US (1) US3593518A (en)
FR (1) FR2018565A1 (en)
GB (1) GB1278590A (en)
SE (1) SE357028B (en)

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3859786A (en) * 1972-05-25 1975-01-14 Ford Motor Co Combustor
US3814575A (en) * 1973-04-25 1974-06-04 Us Air Force Combustion device
US4021186A (en) * 1974-06-19 1977-05-03 Exxon Research And Engineering Company Method and apparatus for reducing NOx from furnaces
GB1481617A (en) * 1974-10-07 1977-08-03 Rolls Royce Gas turbine fuel burners
DE2452178C3 (en) * 1974-11-02 1981-05-07 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Combustion chamber for gas turbine engines
DE2545234C2 (en) * 1975-10-09 1983-09-15 Fa. J. Eberspächer, 7300 Esslingen Mixing device for burners
US4052144A (en) * 1976-03-31 1977-10-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Fuel combustor
DE2839627C2 (en) * 1977-09-13 1983-11-03 Hitachi, Ltd., Tokyo Gas burner
US4276018A (en) * 1979-05-30 1981-06-30 Davey Compressor Co. Mobile heater
US5109671A (en) * 1989-12-05 1992-05-05 Allied-Signal Inc. Combustion apparatus and method for a turbine engine
FR2674317B1 (en) * 1991-03-20 1993-05-28 Snecma COMBUSTION CHAMBER OF A TURBOMACHINE COMPRISING AN ADJUSTMENT OF THE FUEL FLOW.
US5289686A (en) * 1992-11-12 1994-03-01 General Motors Corporation Low nox gas turbine combustor liner with elliptical apertures for air swirling
US5322026A (en) * 1992-12-21 1994-06-21 Bay Il H Waste combustion chamber with tertiary burning zone
GB9726697D0 (en) 1997-12-18 1998-02-18 Secr Defence Fuel injector
US20060130486A1 (en) * 2004-12-17 2006-06-22 Danis Allen M Method and apparatus for assembling gas turbine engine combustors
DE102006041955A1 (en) * 2006-08-30 2008-03-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Method for controlling combustion in a combustion chamber and combustion chamber device
US8171740B2 (en) * 2009-02-27 2012-05-08 Honeywell International Inc. Annular rich-quench-lean gas turbine combustors with plunged holes
US8141365B2 (en) * 2009-02-27 2012-03-27 Honeywell International Inc. Plunged hole arrangement for annular rich-quench-lean gas turbine combustors
US20100242483A1 (en) * 2009-03-30 2010-09-30 United Technologies Corporation Combustor for gas turbine engine
US9222674B2 (en) * 2011-07-21 2015-12-29 United Technologies Corporation Multi-stage amplification vortex mixture for gas turbine engine combustor
CN103032891B (en) * 2013-01-04 2015-07-29 中国科学院工程热物理研究所 A kind of many eddy combustion methods
US20140190171A1 (en) * 2013-01-10 2014-07-10 Honeywell International Inc. Combustors with hybrid walled liners
CA2820365C (en) * 2013-06-25 2021-03-23 Unique Gas Products Ltd. Direct venting system for free-standing propane powered absorption refrigerator
EP3039340B1 (en) * 2013-08-30 2018-11-28 United Technologies Corporation Vena contracta swirling dilution passages for gas turbine engine combustor
US11112115B2 (en) * 2013-08-30 2021-09-07 Raytheon Technologies Corporation Contoured dilution passages for gas turbine engine combustor
US10451281B2 (en) * 2014-11-04 2019-10-22 United Technologies Corporation Low lump mass combustor wall with quench aperture(s)
DE102016201452A1 (en) * 2016-02-01 2017-08-03 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustor with wall contouring
US20180283695A1 (en) * 2017-04-03 2018-10-04 United Technologies Corporation Combustion panel grommet
US11959643B2 (en) * 2021-06-07 2024-04-16 General Electric Company Combustor for a gas turbine engine
US12222104B2 (en) * 2022-03-21 2025-02-11 General Electric Company Turbine engine combustor and combustor liner

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB738006A (en) * 1952-07-12 1955-10-05 Rolls Royce Improvements in or relating to gas turbine engines
US2807933A (en) * 1954-04-01 1957-10-01 Martin Peter Combustion chambers
US2841182A (en) * 1955-12-29 1958-07-01 Westinghouse Electric Corp Boundary layer fluid control apparatus
GB1075958A (en) * 1966-04-29 1967-07-19 Rolls Royce Gas turbine engine

Also Published As

Publication number Publication date
DE1947762A1 (en) 1970-04-02
FR2018565A1 (en) 1970-05-29
SE357028B (en) 1973-06-12
US3593518A (en) 1971-07-20
DE1947762B2 (en) 1975-07-24

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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