GB1060095A - Improvements relating to the flow of a cooling fluid - Google Patents

Improvements relating to the flow of a cooling fluid

Info

Publication number
GB1060095A
GB1060095A GB2002264A GB2002264A GB1060095A GB 1060095 A GB1060095 A GB 1060095A GB 2002264 A GB2002264 A GB 2002264A GB 2002264 A GB2002264 A GB 2002264A GB 1060095 A GB1060095 A GB 1060095A
Authority
GB
United Kingdom
Prior art keywords
adjacent
corrugated
cooling air
annular
sections
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
GB2002264A
Inventor
Edgar George Cowley
Gordon Allan Halls
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 GB2002264A priority Critical patent/GB1060095A/en
Publication of GB1060095A publication Critical patent/GB1060095A/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
    • F23R3/06Arrangement of apertures along the flame tube
    • F23R3/08Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections

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

1, 060, 095. Gas turbine engine combustion chambers. ROLLS-ROYCE Ltd. May 6, 1965 [May 13, 1964], No.20022/64. Heading F1L A gas turbine engine combustion chamber comprises a flame tube formed of a series of tubular sections which overlap at their adjacent ends to provide annular passages through which cooling air may flow so as to provide a film of cooling air over the inner surface of the adjacent downstream section, a corrugated annular member being disposed in the annular passage between adjacent sections, the corrugated member having an inclined end face which extends to the wall of the downstream section which reduces the tendency for the film of cooling air to break away from the surface. In Fig. 2 portions of the adjacent flame tube sections are indicated at 14, 15 and the annular gap therebetween at 26, a corrugated spacer member 30 being disposed in the gap, the downstream end of the corrugated spacer being inclined with respect to the inner surface of the adjacent section as indicated at 33.
GB2002264A 1964-05-13 1964-05-13 Improvements relating to the flow of a cooling fluid Expired GB1060095A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2002264A GB1060095A (en) 1964-05-13 1964-05-13 Improvements relating to the flow of a cooling fluid

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2002264A GB1060095A (en) 1964-05-13 1964-05-13 Improvements relating to the flow of a cooling fluid

Publications (1)

Publication Number Publication Date
GB1060095A true GB1060095A (en) 1967-02-22

Family

ID=10139071

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2002264A Expired GB1060095A (en) 1964-05-13 1964-05-13 Improvements relating to the flow of a cooling fluid

Country Status (1)

Country Link
GB (1) GB1060095A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1989006308A1 (en) * 1987-12-28 1989-07-13 Sundstrand Corporation Annular combustor with tangential cooling air injection
US5327727A (en) * 1993-04-05 1994-07-12 General Electric Company Micro-grooved heat transfer combustor wall
US5337568A (en) * 1993-04-05 1994-08-16 General Electric Company Micro-grooved heat transfer wall
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
US5653110A (en) * 1991-07-22 1997-08-05 General Electric Company Film cooling of jet engine components
US5680767A (en) * 1995-09-11 1997-10-28 General Electric Company Regenerative combustor cooling in a gas turbine engine
CN106705075A (en) * 2016-12-12 2017-05-24 深圳智慧能源技术有限公司 Torch with forced-cooling air film

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1989006308A1 (en) * 1987-12-28 1989-07-13 Sundstrand Corporation Annular combustor with tangential cooling air injection
US4928479A (en) * 1987-12-28 1990-05-29 Sundstrand Corporation Annular combustor with tangential cooling air injection
USRE34962E (en) * 1987-12-28 1995-06-13 Sundstrand Corporation Annular combustor with tangential cooling air injection
US5653110A (en) * 1991-07-22 1997-08-05 General Electric Company Film cooling of jet engine components
US5327727A (en) * 1993-04-05 1994-07-12 General Electric Company Micro-grooved heat transfer combustor wall
US5337568A (en) * 1993-04-05 1994-08-16 General Electric Company Micro-grooved heat transfer wall
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
US5680767A (en) * 1995-09-11 1997-10-28 General Electric Company Regenerative combustor cooling in a gas turbine engine
CN106705075A (en) * 2016-12-12 2017-05-24 深圳智慧能源技术有限公司 Torch with forced-cooling air film
CN106705075B (en) * 2016-12-12 2023-12-12 深圳智慧能源技术有限公司 Forced air film cooling torch

Similar Documents

Publication Publication Date Title
GB1314666A (en) Flame tubes for combustion chambers for gas turbine engines
GB1010338A (en) Means for supporting the downstream end of a combustion chamber in a gas turbine engine
GB1108705A (en) Improvements in cooling structure or combustion chamber
GB790293A (en) Improvements in or relating to heat-resisting wall structures for gas-turbine enginecombustion equipment
GB836088A (en) Improvements in turbojet engine afterburners
GB1138547A (en) Improvements in cooling structure
GB1180706A (en) Flame Tube
GB1344359A (en) Combustion equipment for gas turbine engines
GB1037923A (en) Combustion chamber for a gas turbine
GB1060095A (en) Improvements relating to the flow of a cooling fluid
GB1138679A (en) Wall element for combustion chambers
GB1037955A (en) Cooling arrangement for crossover tubes, linking flame tubes in a combustion chamber
GB836117A (en) Improvements in or relating to combustion equipment for gas-turbine engines
US2996884A (en) Combustion chamber
GB669751A (en) Improvements relating to combustion chambers for gas turbine plants and the like
GB1059199A (en) Flame tube
GB1130371A (en) Improvements in boundary wall structures for hot fluid streams
US2912825A (en) Flameholder with boundary layer control
GB887639A (en) Combustion equipment for a gas turbine engine
GB1055087A (en) Gas turbine engine combustion chamber
GB1289523A (en)
GB1060097A (en) Improvements relating to the flow of a cooling fluid
GB741488A (en) Combustion chambers for jet-propulsion engines, gas turbines and other prime movers
GB776366A (en) Improvements in or relating to combustion equipment of gas-turbine engines
GB1021588A (en) Combustion equipment for a gas turbine engine