FR1493144A - Improvements to combustion devices for gas turbine engines - Google Patents

Improvements to combustion devices for gas turbine engines

Info

Publication number
FR1493144A
FR1493144A FR73534A FR73534A FR1493144A FR 1493144 A FR1493144 A FR 1493144A FR 73534 A FR73534 A FR 73534A FR 73534 A FR73534 A FR 73534A FR 1493144 A FR1493144 A FR 1493144A
Authority
FR
France
Prior art keywords
gas turbine
turbine engines
combustion devices
combustion
devices
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
FR73534A
Other languages
French (fr)
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries Ltd
Joseph Lucas Industries 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
Application filed by Lucas Industries Ltd, Joseph Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to FR73534A priority Critical patent/FR1493144A/en
Application granted granted Critical
Publication of FR1493144A publication Critical patent/FR1493144A/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
FR73534A 1966-08-19 1966-08-19 Improvements to combustion devices for gas turbine engines Expired FR1493144A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR73534A FR1493144A (en) 1966-08-19 1966-08-19 Improvements to combustion devices for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR73534A FR1493144A (en) 1966-08-19 1966-08-19 Improvements to combustion devices for gas turbine engines

Publications (1)

Publication Number Publication Date
FR1493144A true FR1493144A (en) 1967-08-25

Family

ID=8615636

Family Applications (1)

Application Number Title Priority Date Filing Date
FR73534A Expired FR1493144A (en) 1966-08-19 1966-08-19 Improvements to combustion devices for gas turbine engines

Country Status (1)

Country Link
FR (1) FR1493144A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0890795A3 (en) * 1997-07-07 2000-03-22 General Electric Company Rapid-quench axially staged combustor
EP0943868A3 (en) * 1998-03-18 2000-03-22 General Electric Company Gas turbine combustor
JP2001193484A (en) * 1999-10-14 2001-07-17 General Electric Co <Ge> Film-cooling combustor liner and manufacturing method thereof
EP1001222A3 (en) * 1998-11-13 2002-03-20 General Electric Company Multi-hole film cooled combustor liner
FR2892180A1 (en) * 2005-10-18 2007-04-20 Snecma Sa IMPROVING THE PERFOMANCE OF A COMBUSTION CHAMBER BY MULTIPERFORATING THE WALLS
JP2009103438A (en) * 2007-10-22 2009-05-14 Snecma Combustion chamber with optimized dilution and turbomachine provided with the same
RU2449219C2 (en) * 2006-09-12 2012-04-27 Дженерал Электрик Компани Structure with mixing holes and method to improve homogeneity of fuel and air mixture in combustion chamber (versions)
JP2016106210A (en) * 2009-09-21 2016-06-16 スネクマ Combustion chamber for aircraft turbine engine having combustion hole of different form

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0890795A3 (en) * 1997-07-07 2000-03-22 General Electric Company Rapid-quench axially staged combustor
EP0943868A3 (en) * 1998-03-18 2000-03-22 General Electric Company Gas turbine combustor
US6192689B1 (en) 1998-03-18 2001-02-27 General Electric Company Reduced emissions gas turbine combustor
EP1001222A3 (en) * 1998-11-13 2002-03-20 General Electric Company Multi-hole film cooled combustor liner
JP2001193484A (en) * 1999-10-14 2001-07-17 General Electric Co <Ge> Film-cooling combustor liner and manufacturing method thereof
FR2892180A1 (en) * 2005-10-18 2007-04-20 Snecma Sa IMPROVING THE PERFOMANCE OF A COMBUSTION CHAMBER BY MULTIPERFORATING THE WALLS
EP1777458A1 (en) * 2005-10-18 2007-04-25 Snecma Improvement of the performances of a combustion chamber by multiperforating the walls
US7748222B2 (en) 2005-10-18 2010-07-06 Snecma Performance of a combustion chamber by multiple wall perforations
RU2449219C2 (en) * 2006-09-12 2012-04-27 Дженерал Электрик Компани Structure with mixing holes and method to improve homogeneity of fuel and air mixture in combustion chamber (versions)
JP2009103438A (en) * 2007-10-22 2009-05-14 Snecma Combustion chamber with optimized dilution and turbomachine provided with the same
JP2016106210A (en) * 2009-09-21 2016-06-16 スネクマ Combustion chamber for aircraft turbine engine having combustion hole of different form

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