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GB685068A - Combustion chamber for gas turbines - Google Patents

Combustion chamber for gas turbines

Info

Publication number
GB685068A
GB685068A GB7072/50A GB707250A GB685068A GB 685068 A GB685068 A GB 685068A GB 7072/50 A GB7072/50 A GB 7072/50A GB 707250 A GB707250 A GB 707250A GB 685068 A GB685068 A GB 685068A
Authority
GB
United Kingdom
Prior art keywords
air
orifices
burner
upstream
shroud
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
GB7072/50A
Inventor
Isaac Lubbock
Roy Michael Palmer
Harold Rowling
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.)
Shell Refining and Marketing Co Ltd
Original Assignee
Shell Refining and Marketing Co 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
Priority to BE502037D priority Critical patent/BE502037A/xx
Application filed by Shell Refining and Marketing Co Ltd filed Critical Shell Refining and Marketing Co Ltd
Priority to GB7072/50A priority patent/GB685068A/en
Priority to FR1037635D priority patent/FR1037635A/en
Priority to DES22437A priority patent/DE876495C/en
Publication of GB685068A publication Critical patent/GB685068A/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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)

Abstract

685,068. Generating combustion products under pressure. SHELL REFINING & MARKETING CO., Ltd. Feb. 26, 1951 [March 21, 1950], No. 7072/50. Class 51 (i). In an air-jacketed type of combustion chamber for a gas turbine engine, the flame tube comprises a cylindrical portion 8 within which the burner 17 is disposed, and a tubular wall 9 of greater diameter than the portion 8, the wall 9 and portion 8 being connected by a divergent wall 10. A shroud 13 surrounds the burner to form an annular channel through which a substantial though minor portion of the combustion air is admitted, and an air swirler 12 is disposed around the shroud through which the remainder of the combustion air is admitted. The part of the tubular wall 9 which surrounds the flame 18 is substantially imperforate, but the portion downstream of the flame is provided with orifices 19-22 through which dilution or tertiary air is admitted. The shroud 13 is closed at its upstream end and has ports 14 in its wall for the admission of combustion air ; the downstream end is formed with a converging lip 15. The relative axial positions of the burner and shroud may be adjustable. The upstream rows of orifices 19, 20 are elongated and their longitudinal axes are inclined to the axis of the flame tube at the same angle as that which the current of gases inside the flame tube makes with the axis thereof. The upstream rows of dilution air orifices may alternatively be provided with chutes or with an obturator ring of U-shaped section disposed around the downstream edges of the orifices. A bleed tube may be disposed around the burner to permit a small flow of air around the tip of the burner to keep it clean. Combustion air may be admitted through the open upstream end of the sleeve 13 instead of through ports 14, and a disc-shaped baffle is then disposed upstream of the open end. Some or all of the dilution air orifices may have short pipes projecting radially or tangentially into the interior of the flame tube and the pipes may be double-walled. The orifices may also have trough-like baffles with their open sides facing upstream as in Specification 676,473.
GB7072/50A 1950-03-21 1950-03-21 Combustion chamber for gas turbines Expired GB685068A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
BE502037D BE502037A (en) 1950-03-21
GB7072/50A GB685068A (en) 1950-03-21 1950-03-21 Combustion chamber for gas turbines
FR1037635D FR1037635A (en) 1950-03-21 1951-03-21 Combustion chamber for gas turbines
DES22437A DE876495C (en) 1950-03-21 1951-03-21 Combustion chamber for gas turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7072/50A GB685068A (en) 1950-03-21 1950-03-21 Combustion chamber for gas turbines

Publications (1)

Publication Number Publication Date
GB685068A true GB685068A (en) 1952-12-31

Family

ID=9826082

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7072/50A Expired GB685068A (en) 1950-03-21 1950-03-21 Combustion chamber for gas turbines

Country Status (4)

Country Link
BE (1) BE502037A (en)
DE (1) DE876495C (en)
FR (1) FR1037635A (en)
GB (1) GB685068A (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3092964A (en) * 1954-03-30 1963-06-11 Martin Peter Method of relighting in combustion chambers
DE1211863B (en) * 1962-02-01 1966-03-03 Rolls Royce Combustion chamber for gas turbine engines
US3788065A (en) * 1970-10-26 1974-01-29 United Aircraft Corp Annular combustion chamber for dissimilar fluids in swirling flow relationship
US5050385A (en) * 1982-10-06 1991-09-24 Hitachi, Ltd. Inner cylinder for a gas turbine combustor reinforced by built up welding
EP0676590A1 (en) * 1994-04-08 1995-10-11 ROLLS-ROYCE plc Gas turbine engine combustion apparatus
JP2002155759A (en) * 2000-11-20 2002-05-31 General Electric Co <Ge> Aerodynamic device and related method for strengthening side plate cooling of collision cooling transition duct
GB2461542A (en) * 2008-07-03 2010-01-06 Rolls Royce Plc Combustion Arrangement with Dilution Ports and Associated Cooling Air Trim Ports
FR2948987A1 (en) * 2009-08-04 2011-02-11 Snecma Combustion chamber for e.g. jet engine, of airplane, has inlet openings with oblong shape, so that maximum space between two points of edge of projections is greater than maximum space between two other points of edge of projections
FR2958012A1 (en) * 2010-03-23 2011-09-30 Snecma Annular combustion chamber for use between upstream high pressure compressor and downstream high pressure turbine of airplane, has rotary walls comprising orifices whose axis is inclined with respect to axis of chamber at specific angle
CN102472492A (en) * 2009-08-04 2012-05-23 斯奈克玛 Turbomachine combustion chamber with improved air inlet
CN103562500A (en) * 2011-03-29 2014-02-05 西门子能量股份有限公司 Turbine combustion system cooling scoop
CN106969381A (en) * 2017-03-27 2017-07-21 南京航空航天大学 Adjustable cyclone coupling spray nozzle
EP3258066A1 (en) * 2016-06-16 2017-12-20 Doosan Heavy Industries & Construction Co., Ltd. Air flow guide cap and combustion duct having the same
CN109737450A (en) * 2018-12-11 2019-05-10 北京航空航天大学 Combustion chamber combustion oscillation control device and combustion chamber combustion oscillation control method

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1108517B (en) * 1957-09-27 1961-06-08 Rolls Royce Gas turbine combustor
DE1123868B (en) * 1958-08-26 1962-02-15 Schweizerische Lokomotiv Combustion chamber, especially for gas turbines
DE1284157B (en) * 1963-12-04 1968-11-28 Rolls Royce Combustion device for gas turbine engines
DE2808874C2 (en) * 1978-03-02 1985-01-24 Smit Ovens Nijmegen B.V., Nijmegen Device for the combustion of combustible substances entrained in a gas stream or for heating air
US4702073A (en) * 1986-03-10 1987-10-27 Melconian Jerry O Variable residence time vortex combustor
US5289686A (en) * 1992-11-12 1994-03-01 General Motors Corporation Low nox gas turbine combustor liner with elliptical apertures for air swirling

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3092964A (en) * 1954-03-30 1963-06-11 Martin Peter Method of relighting in combustion chambers
DE1211863B (en) * 1962-02-01 1966-03-03 Rolls Royce Combustion chamber for gas turbine engines
US3788065A (en) * 1970-10-26 1974-01-29 United Aircraft Corp Annular combustion chamber for dissimilar fluids in swirling flow relationship
US5050385A (en) * 1982-10-06 1991-09-24 Hitachi, Ltd. Inner cylinder for a gas turbine combustor reinforced by built up welding
EP0676590A1 (en) * 1994-04-08 1995-10-11 ROLLS-ROYCE plc Gas turbine engine combustion apparatus
US5590530A (en) * 1994-04-08 1997-01-07 Rolls-Royce Plc Fuel and air mixing parts for a turbine combustion chamber
JP2002155759A (en) * 2000-11-20 2002-05-31 General Electric Co <Ge> Aerodynamic device and related method for strengthening side plate cooling of collision cooling transition duct
EP1207273A3 (en) * 2000-11-20 2002-11-20 General Electric Company Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method
EP2813761A3 (en) * 2000-11-20 2015-01-07 General Electric Company Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct
GB2461542A (en) * 2008-07-03 2010-01-06 Rolls Royce Plc Combustion Arrangement with Dilution Ports and Associated Cooling Air Trim Ports
GB2461542B (en) * 2008-07-03 2010-10-13 Rolls Royce Plc Combustion Arrangement with Dilution and Trim Ports
CN102472492A (en) * 2009-08-04 2012-05-23 斯奈克玛 Turbomachine combustion chamber with improved air inlet
FR2948987A1 (en) * 2009-08-04 2011-02-11 Snecma Combustion chamber for e.g. jet engine, of airplane, has inlet openings with oblong shape, so that maximum space between two points of edge of projections is greater than maximum space between two other points of edge of projections
CN102472492B (en) * 2009-08-04 2015-05-06 斯奈克玛 Combustion chamber for a turbine engine having improved air inlets
US9175856B2 (en) 2009-08-04 2015-11-03 Snecma Combustion chamber for a turbomachine including improved air inlets
FR2958012A1 (en) * 2010-03-23 2011-09-30 Snecma Annular combustion chamber for use between upstream high pressure compressor and downstream high pressure turbine of airplane, has rotary walls comprising orifices whose axis is inclined with respect to axis of chamber at specific angle
CN103562500A (en) * 2011-03-29 2014-02-05 西门子能量股份有限公司 Turbine combustion system cooling scoop
CN103562500B (en) * 2011-03-29 2016-08-24 西门子能量股份有限公司 Turbine combustion system cooling dome
US10520192B2 (en) 2016-06-16 2019-12-31 DOOSAN Heavy Industries Construction Co., LTD Air flow guide cap and combustion duct having the same
EP3258066A1 (en) * 2016-06-16 2017-12-20 Doosan Heavy Industries & Construction Co., Ltd. Air flow guide cap and combustion duct having the same
JP2017223214A (en) * 2016-06-16 2017-12-21 ドゥサン ヘヴィー インダストリーズ アンド コンストラクション カンパニー リミテッド Air guiding cap, and combustion duct having the same
CN106969381A (en) * 2017-03-27 2017-07-21 南京航空航天大学 Adjustable cyclone coupling spray nozzle
CN106969381B (en) * 2017-03-27 2023-09-26 南京航空航天大学 Adjustable cyclone coupling nozzle
CN109737450B (en) * 2018-12-11 2019-12-03 北京航空航天大学 Combustion chambers burn oscillation control device and combustion chambers burn oscillation control method
CN109737450A (en) * 2018-12-11 2019-05-10 北京航空航天大学 Combustion chamber combustion oscillation control device and combustion chamber combustion oscillation control method

Also Published As

Publication number Publication date
DE876495C (en) 1953-05-15
FR1037635A (en) 1953-09-22
BE502037A (en)

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