GB947808A - Combustion chamber for a gas turbine engine - Google Patents

Combustion chamber for a gas turbine engine

Info

Publication number
GB947808A
GB947808A GB28322/61A GB2832261A GB947808A GB 947808 A GB947808 A GB 947808A GB 28322/61 A GB28322/61 A GB 28322/61A GB 2832261 A GB2832261 A GB 2832261A GB 947808 A GB947808 A GB 947808A
Authority
GB
United Kingdom
Prior art keywords
fuel
combustion chamber
gas turbine
combustion
nozzle
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
GB28322/61A
Inventor
Denis Richard Carlisle
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 GB28322/61A priority Critical patent/GB947808A/en
Priority to DER33207A priority patent/DE1202064B/en
Priority to FR905829A priority patent/FR1330443A/en
Priority to US252853A priority patent/US3142961A/en
Publication of GB947808A publication Critical patent/GB947808A/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
    • 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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • 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)
  • Fuel-Injection Apparatus (AREA)
  • Spray-Type Burners (AREA)

Abstract

947,808. Gas turbine combustion chambers. ROLLS-ROYCE Ltd. July 27, 1962 [Aug. 3, 1961], No. 28322/61. Heading F1L. A combustion chamber for a gas turbine engine comprises a fuel injection nozzle mounted within the chamber and a fuel impingement member extending longitudinally therein such that the fuel from the nozzle is directed on to the upstream portion of the member, and means for directing combustion air to urge fuel downstream along the member to effect atomization of the fuel, deflector means being provided at the downstream end of the member for reducing the velocity of the fuel and deflecting it so that it leaves the member transversely. An annular combustion chamber has walls 15, 17 and dilution and cooling air ducts 19, 20 respectively. An annular manifold 24 having a supply pipe 25 feeds fuel to injection nozzles 26 extending into the combustion air duct 22. Each nozzle 26 is associated with a rectangular fuel impingement plate 27 mounted on the duct 22 by a strap 30 and having an open gutter 31 at its downstream end. Angularly spaced apart baffles 34 are mounted on either side of each impingement plate 27 to direct air past the plate 27 and urge the fuel downstream into the gutter 31. Dilution air enters the combustion chamber 13 through angularly spaced apart holes 23. Fuel is also supplied through two auxiliary atomizing nozzles 37 having igniters 40.
GB28322/61A 1961-08-03 1961-08-03 Combustion chamber for a gas turbine engine Expired GB947808A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB28322/61A GB947808A (en) 1961-08-03 1961-08-03 Combustion chamber for a gas turbine engine
DER33207A DE1202064B (en) 1961-08-03 1962-07-26 Combustion chamber for gas turbine engines
FR905829A FR1330443A (en) 1961-08-03 1962-08-01 Combustion chamber for gas turbo-engine
US252853A US3142961A (en) 1961-08-03 1963-01-21 Combustion chamber for a gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB28322/61A GB947808A (en) 1961-08-03 1961-08-03 Combustion chamber for a gas turbine engine

Publications (1)

Publication Number Publication Date
GB947808A true GB947808A (en) 1964-01-29

Family

ID=10273838

Family Applications (1)

Application Number Title Priority Date Filing Date
GB28322/61A Expired GB947808A (en) 1961-08-03 1961-08-03 Combustion chamber for a gas turbine engine

Country Status (2)

Country Link
DE (1) DE1202064B (en)
GB (1) GB947808A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1270328B (en) * 1964-02-21 1968-06-12 Rolls Royce Combustion chamber for a gas turbine jet engine
CN105593602A (en) * 2013-10-01 2016-05-18 斯奈克玛 Combustion chamber for turbine engine with homogeneous air intake through fuel-injection systems

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH246172A (en) * 1915-05-22 1946-12-15 Escher Wyss Maschf Ag Method for operating combustion chambers with high thermal loads for gas turbine plants, and device for carrying out this method.
US2560207A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners
GB840529A (en) * 1957-06-20 1960-07-06 Rolls Royce Improvements in or relating to combustion equipment of gas turbine engines
FR1251927A (en) * 1960-03-25 1961-01-20 Maschf Augsburg Nuernberg Ag Method and device for operating an internal combustion engine with continuous or discontinuous work

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1270328B (en) * 1964-02-21 1968-06-12 Rolls Royce Combustion chamber for a gas turbine jet engine
CN105593602A (en) * 2013-10-01 2016-05-18 斯奈克玛 Combustion chamber for turbine engine with homogeneous air intake through fuel-injection systems
CN105593602B (en) * 2013-10-01 2018-07-24 斯奈克玛 Pass through the combustion chamber of the turbogenerator of the uniform air inlet of fuel injection system

Also Published As

Publication number Publication date
DE1202064B (en) 1965-09-30

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