GB1039677A - Combustion chamber for a gas turbine engine - Google Patents

Combustion chamber for a gas turbine engine

Info

Publication number
GB1039677A
GB1039677A GB2743163A GB2743163A GB1039677A GB 1039677 A GB1039677 A GB 1039677A GB 2743163 A GB2743163 A GB 2743163A GB 2743163 A GB2743163 A GB 2743163A GB 1039677 A GB1039677 A GB 1039677A
Authority
GB
United Kingdom
Prior art keywords
gutters
combustion
gas turbine
disc
rotation
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
GB2743163A
Inventor
Geoffrey Light Wilde
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 GB2743163A priority Critical patent/GB1039677A/en
Priority to DE1964R0038305 priority patent/DE1246324B/en
Publication of GB1039677A publication Critical patent/GB1039677A/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
    • F23R3/16—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
    • 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
    • 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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Supercharger (AREA)

Abstract

1,039,677. Gas turbine combustion chambers; gas turbine plant. ROLLS-ROYCE Ltd. June 17, 1964 [July 10, 1963], No. 27431/63. Headings F1G, F1L and FIT. An annular gas turbine engine combustion chamber comprises radially extending combustion stabilizing means mounted in the chamber for rotation about the longitudinal axis thereof, the stabilizers being formed or provided with means to ensure rotation thereof throughout the operation of the engine, means for supplying fuel to a combustion zone adjacent and on the downstream side of the stabilizers, and guide means for ensuring that combustion air in the combustion zone has a substantial circumferential component of velocity in the same angular sense as the direction of rotation of the stabilizers. An annular gas turbine engine combustion chamber 14, Fig. 2, comprises rotating V-shaped combustion stabilizing gutters 23 mounted on a rotor disc 22 connected to the high pressure turbine shaft 20. Each of the gutters 23 has limbs 24, 25, Figs. 3,4. Free vortex airflow past the gutters 23 is imparted by guide vanes 35, the flow having a substantial circumferential velocity component in the direction of rotation of the gutters. To conform with the flow the gutters are twisted so as to face axially at the root 26 and circumferentially at the tip 27. A radial primary fuel channel 30 is drilled in each gutter 23 and communicates with the combustion zone downstream through drillings 31. An annular fuel reservoir 32 on disc 22 is supplied through pipe 33 and feeds fuel centrifugally to channels 30. Main fuel injectors 29 may also be carried on disc 22 between pairs of gutters 23. Additional fixed injectors 34 may be provided. In a modification Fig. 6 (not shown), disc 22 is freely mounted in bearings upon shaft 20 and is rotated by the air passing through combustion chamber 14. In a further modification, disc 22 is driven by reduction gearing from shaft 20.
GB2743163A 1963-07-10 1963-07-10 Combustion chamber for a gas turbine engine Expired GB1039677A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB2743163A GB1039677A (en) 1963-07-10 1963-07-10 Combustion chamber for a gas turbine engine
DE1964R0038305 DE1246324B (en) 1963-07-10 1964-07-07 Combustion chamber for gas turbine jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2743163A GB1039677A (en) 1963-07-10 1963-07-10 Combustion chamber for a gas turbine engine

Publications (1)

Publication Number Publication Date
GB1039677A true GB1039677A (en) 1966-08-17

Family

ID=10259486

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2743163A Expired GB1039677A (en) 1963-07-10 1963-07-10 Combustion chamber for a gas turbine engine

Country Status (2)

Country Link
DE (1) DE1246324B (en)
GB (1) GB1039677A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2629872A1 (en) * 1988-04-11 1989-10-13 Aris Spa MODULAR LIGHT TURBOREACTOR
RU2531110C2 (en) * 2010-06-29 2014-10-20 Дженерал Электрик Компани Gas-turbine unit and unit with injector vanes (versions)
CN113279857A (en) * 2021-05-27 2021-08-20 中国科学院工程热物理研究所 High thrust-weight ratio gas turbine generator suitable for unmanned aerial vehicle

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1235583A (en) * 1983-06-20 1988-04-26 Marius A. Paul Processes of intensification of the thermoenergetical cycle and air jet propulsion engines
US5177954A (en) * 1984-10-10 1993-01-12 Paul Marius A Gas turbine engine with cooled turbine blades
US5122033A (en) * 1990-11-16 1992-06-16 Paul Marius A Turbine blade unit
DE19507763A1 (en) * 1995-03-06 1996-09-12 Siemens Ag Method and device for burning a fuel in a gas turbine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE768038C (en) * 1938-08-27 1955-05-26 Messerschmitt Boelkow Blohm Device for fuel injection into an air stream of variable speed while maintaining the same mixing ratio
DE768104C (en) * 1938-12-06 1955-08-04 Messerschmitt Boelkow Blohm Device with rotatable fuel container for injecting fuel into an air stream of variable speed
GB749904A (en) * 1952-06-23 1956-06-06 Parsons C A & Co Ltd Improvements in and relating to heating units for combustion turbines
US3088281A (en) * 1956-04-03 1963-05-07 Bristol Siddeley Engines Ltd Combustion chambers for use with swirling combustion supporting medium
FR1166154A (en) * 1957-02-01 1958-11-04 Snecma Semi-vaporization burner
US2875580A (en) * 1957-04-16 1959-03-03 Westinghouse Electric Corp Flameholding apparatus
FR76734E (en) * 1959-12-14 1961-11-24 Bristol Aero Engines Ltd Improvements to combustion chambers
US3009317A (en) * 1960-04-20 1961-11-21 Robert E Meyer High energy fuel afterburner system

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2629872A1 (en) * 1988-04-11 1989-10-13 Aris Spa MODULAR LIGHT TURBOREACTOR
RU2531110C2 (en) * 2010-06-29 2014-10-20 Дженерал Электрик Компани Gas-turbine unit and unit with injector vanes (versions)
CN113279857A (en) * 2021-05-27 2021-08-20 中国科学院工程热物理研究所 High thrust-weight ratio gas turbine generator suitable for unmanned aerial vehicle

Also Published As

Publication number Publication date
DE1246324B (en) 1967-08-03

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