GB836117A - Improvements in or relating to combustion equipment for gas-turbine engines - Google Patents

Improvements in or relating to combustion equipment for gas-turbine engines

Info

Publication number
GB836117A
GB836117A GB338156A GB338156A GB836117A GB 836117 A GB836117 A GB 836117A GB 338156 A GB338156 A GB 338156A GB 338156 A GB338156 A GB 338156A GB 836117 A GB836117 A GB 836117A
Authority
GB
United Kingdom
Prior art keywords
flame tube
air
disposed
centre line
scoops
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
GB338156A
Inventor
Frederick Reginald Murray
Francis Murray Johnson
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 GB338156A priority Critical patent/GB836117A/en
Publication of GB836117A publication Critical patent/GB836117A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/045Air inlet arrangements using pipes

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)

Abstract

836,117. Generating combustion products under pressure. ROLLS-ROYCE Ltd. Feb. 4, 1957 [Feb. 2, 1956], No. 3381/56. Class 51 (1). Combustion equipment of a gas turbine engine comprises a flame tube disposed within an outer air casing, a fuel injector being provided to inject fuel into the upstream end of the flame tube. The flame tube has at each side of the local centre line of the combustion space air inlet means adapted to direct into the combustion space a plurality of streams of air having a component of velocity in an upstream direction to meet in the region of the local centre line, the air streams from each respective side of the local centre line being directed to meet at a point short of the local centre line so as to produce an air stream which is flattened in cross-section to reduce the risk of this air stream missing the flattened air stream from the air inlet means on the opposite side of the local centre line. The combustion equipment shown comprises an annular flame tube 24, 25 disposed within an outer annular air casing 22, 23, a fuel injector 20 being disposed within the upstream portion of the flame tube 14, 15 and injecting through an aperture 21 in a ring member 17, the flanges 17a, 17b of which are spaced from the walls of the flame tube by corrugated spacers 18, 19. Pairs of U-shaped scoop members 31, 34 in nested relation are disposed on the outer surfaces of the flame tube walls, the scoops facing into the air streams flowing between the flame tube and outer air casing. The scoop members 31 are curved at their downstream ends to enter orifices formed in the flame tube wall sections 24a, 25a, the adjacent portions of the flame tube wall sections being curved inwardly at 33. A curved tubular member 36 is disposed within each scoop member 34 and extends through an opening in the flame tube wall section 24a, 25a. The air streams from each pair of scoops converge at a point which lies short of the local centre line 30 of the combustion space. The air streams from the scoops at each side meet adjacent the centre line. The cross-section through the scoops in this embodiment is constant whereby velocity of the air streams remains constant. In a second embodiment, annular scoops are disposed on the outer surfaces of the flame tube walls, the crosssectional area of the scoops increasing in the direction of air flow. Short pipes directed in an upstream direction lead from openings formed in the flame tube wall at the downstream end of each scoop, the air streams from each pair of pipes converging at a point short of the local centre-line of the combustion space. The invention is also applicable in the case of combustion equipment comprising tubular flame tubes disposed either each in its own tubular air casing or a plurality thereof disposed in an annular air casing. Specifications 744,593, 744,657 and 744,659 are referred to.
GB338156A 1956-02-02 1956-02-02 Improvements in or relating to combustion equipment for gas-turbine engines Expired GB836117A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB338156A GB836117A (en) 1956-02-02 1956-02-02 Improvements in or relating to combustion equipment for gas-turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB338156A GB836117A (en) 1956-02-02 1956-02-02 Improvements in or relating to combustion equipment for gas-turbine engines

Publications (1)

Publication Number Publication Date
GB836117A true GB836117A (en) 1960-06-01

Family

ID=9757260

Family Applications (1)

Application Number Title Priority Date Filing Date
GB338156A Expired GB836117A (en) 1956-02-02 1956-02-02 Improvements in or relating to combustion equipment for gas-turbine engines

Country Status (1)

Country Link
GB (1) GB836117A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3338051A (en) * 1965-05-28 1967-08-29 United Aircraft Corp High velocity ram induction burner
US3643430A (en) * 1970-03-04 1972-02-22 United Aircraft Corp Smoke reduction combustion chamber
US3751911A (en) * 1970-04-18 1973-08-14 Motoren Turbinen Union Air inlet arrangement for gas turbine engine combustion chamber
FR2222124A1 (en) * 1973-03-23 1974-10-18 Pillard Chauffage Combustion gases homogenizing equipment - ensures uniform temperatures for drying plants, gas turbines and jet engines
JPS5287510A (en) * 1976-01-17 1977-07-21 Koukuu Uchiyuu Gijiyutsu Kenki Gas turbine combustor
USRE30160E (en) * 1970-03-04 1979-11-27 United Technologies Corporation Smoke reduction combustion chamber
US4301657A (en) * 1978-05-04 1981-11-24 Caterpillar Tractor Co. Gas turbine combustion chamber
WO1982000334A1 (en) * 1980-07-10 1982-02-04 Bailey J Vaporizing combustor tube
EP2141329A2 (en) 2008-07-03 2010-01-06 United Technologies Corporation Impingement cooling device
EP2966356A1 (en) * 2014-07-10 2016-01-13 Alstom Technology Ltd Sequential combustor arrangement with a mixer
EP3702668A1 (en) * 2019-02-28 2020-09-02 Rolls-Royce plc Combustion liner and gas turbine engine comprising a combustion liner

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3338051A (en) * 1965-05-28 1967-08-29 United Aircraft Corp High velocity ram induction burner
DE1526882B1 (en) * 1965-05-28 1971-07-01 United Aircraft Corp COMBUSTION DEVICE FOR A GAS TURBINE ENGINE
US3643430A (en) * 1970-03-04 1972-02-22 United Aircraft Corp Smoke reduction combustion chamber
USRE30160E (en) * 1970-03-04 1979-11-27 United Technologies Corporation Smoke reduction combustion chamber
US3751911A (en) * 1970-04-18 1973-08-14 Motoren Turbinen Union Air inlet arrangement for gas turbine engine combustion chamber
FR2222124A1 (en) * 1973-03-23 1974-10-18 Pillard Chauffage Combustion gases homogenizing equipment - ensures uniform temperatures for drying plants, gas turbines and jet engines
JPS5287510A (en) * 1976-01-17 1977-07-21 Koukuu Uchiyuu Gijiyutsu Kenki Gas turbine combustor
US4301657A (en) * 1978-05-04 1981-11-24 Caterpillar Tractor Co. Gas turbine combustion chamber
WO1982000334A1 (en) * 1980-07-10 1982-02-04 Bailey J Vaporizing combustor tube
EP2141329A2 (en) 2008-07-03 2010-01-06 United Technologies Corporation Impingement cooling device
EP2141329A3 (en) * 2008-07-03 2013-03-06 United Technologies Corporation Impingement cooling device
US9046269B2 (en) 2008-07-03 2015-06-02 Pw Power Systems, Inc. Impingement cooling device
EP2966356A1 (en) * 2014-07-10 2016-01-13 Alstom Technology Ltd Sequential combustor arrangement with a mixer
CN105258157A (en) * 2014-07-10 2016-01-20 阿尔斯通技术有限公司 Sequential combustor arrangement with a mixer
US10215417B2 (en) 2014-07-10 2019-02-26 Ansaldo Energia Switzerland AG Sequential combustor arrangement with a mixer
CN105258157B (en) * 2014-07-10 2019-11-05 安萨尔多能源瑞士股份公司 Sequential combustion device assembly with mixer
EP3702668A1 (en) * 2019-02-28 2020-09-02 Rolls-Royce plc Combustion liner and gas turbine engine comprising a combustion liner

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