GB812201A - Improvements in combustion equipment for continuous-flow internal combustion engines - Google Patents

Improvements in combustion equipment for continuous-flow internal combustion engines

Info

Publication number
GB812201A
GB812201A GB30168/56A GB3016856A GB812201A GB 812201 A GB812201 A GB 812201A GB 30168/56 A GB30168/56 A GB 30168/56A GB 3016856 A GB3016856 A GB 3016856A GB 812201 A GB812201 A GB 812201A
Authority
GB
United Kingdom
Prior art keywords
flame tube
walls
combustion
equipment
wall
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
GB30168/56A
Inventor
Hans Hering
Lothar Menz
Edouard Caffier
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB812201A publication Critical patent/GB812201A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
  • Measuring Fluid Pressure (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

812,201. Generating combustion products under pressure. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Oct. 3, 1956 [Oct. 28, 1955], No. 30168/56. Class 51 (1). In combustion equipment, for example of a gas turbine engine, cornprising a flame tube 2 disposed within an outer casing 1a, the upstream portion of the flame tube is provided with a primary air inlet passage 7 and with fuel injecting means 6 and comprises an unapertured wall (or walls) which separates (or separate) the primary combustion space within the flame tube from the secondary air passage between the flame tube and the outer casing. The wall, or walls, is or are shaped so as to form a restricted outlet 8 at the downstream end of the primary combustion space and the wall, or walls, extends or extend downstream of the restricted outlet by a divergent portion 9 through which are provided secondary air inlet ports 10. The combustion equipment shown in Fig. 1 is of the tubular type but the arrangement shown may also be applied in the case of annular-type equipment. Turbine inlet nozzle guide vanes are indicated at d. In a second embodiment, two restricted portions such as 8 in Fig. 1 are provided at intermediate points along the length of the flame tube. In an annular type of combustion equipment, the inner and outer walls of the flame tube are each provided with a circumferential portion projecting towards the peripheral axis of the flame tube, the two projecting portions being disposed at different points along the length of the flame tube.
GB30168/56A 1955-10-28 1956-10-03 Improvements in combustion equipment for continuous-flow internal combustion engines Expired GB812201A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1135017T 1955-10-28

Publications (1)

Publication Number Publication Date
GB812201A true GB812201A (en) 1959-04-22

Family

ID=9639615

Family Applications (1)

Application Number Title Priority Date Filing Date
GB30168/56A Expired GB812201A (en) 1955-10-28 1956-10-03 Improvements in combustion equipment for continuous-flow internal combustion engines

Country Status (4)

Country Link
US (1) US3082603A (en)
BE (1) BE551418A (en)
FR (1) FR1135017A (en)
GB (1) GB812201A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0845639A1 (en) * 1996-11-29 1998-06-03 Abb Research Ltd. Combustor

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS548890B1 (en) * 1971-04-01 1979-04-19
FR2406075A1 (en) * 1977-10-11 1979-05-11 Snecma COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS
US4265615A (en) * 1978-12-11 1981-05-05 United Technologies Corporation Fuel injection system for low emission burners
US5323605A (en) * 1990-10-01 1994-06-28 General Electric Company Double dome arched combustor
JPH094825A (en) * 1995-06-21 1997-01-10 Mitsubishi Heavy Ind Ltd Combustor
US6021570A (en) * 1997-11-20 2000-02-08 Caterpillar Inc. Annular one piece combustor liner
US6729141B2 (en) * 2002-07-03 2004-05-04 Elliot Energy Systems, Inc. Microturbine with auxiliary air tubes for NOx emission reduction
GB2441342B (en) * 2006-09-01 2009-03-18 Rolls Royce Plc Wall elements with apertures for gas turbine engine components
JP2011102669A (en) 2009-11-10 2011-05-26 Mitsubishi Heavy Ind Ltd Gas turbine combustor and gas turbine
US8707708B2 (en) * 2010-02-22 2014-04-29 United Technologies Corporation 3D non-axisymmetric combustor liner
EP2420730B1 (en) * 2010-08-16 2018-03-07 Ansaldo Energia IP UK Limited Reheat burner
US11747019B1 (en) * 2022-09-02 2023-09-05 General Electric Company Aerodynamic combustor liner design for emissions reductions

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR962581A (en) * 1950-06-16
US945967A (en) * 1909-07-14 1910-01-11 Julius A Mahr Oil-burner.
US2546432A (en) * 1944-03-20 1951-03-27 Power Jets Res & Dev Ltd Apparatus for deflecting a fuel jet towards a region of turbulence in a propulsive gaseous stream
BE466639A (en) * 1944-12-13
BE485523A (en) * 1947-11-03
US2644512A (en) * 1949-06-13 1953-07-07 Heizmotoren Ges Uberlingen Am Burner device having heat exchange and gas flow control means for maintaining pyrophoric ignition therein
US2828609A (en) * 1950-04-03 1958-04-01 Bristol Aero Engines Ltd Combustion chambers including suddenly enlarged chamber portions
GB687667A (en) * 1950-04-03 1953-02-18 Bristol Aeroplane Co Ltd Improvements in or relating to combustion systems
US2825202A (en) * 1950-06-19 1958-03-04 Snecma Pipes traversed by pulsating flow gases
US2699648A (en) * 1950-10-03 1955-01-18 Gen Electric Combustor sectional liner structure with annular inlet nozzles
GB726491A (en) * 1952-07-16 1955-03-16 Onera (Off Nat Aerospatiale) Improvements in internal combustion engines through which a continuous gaseous stream is flowing and in particular in turbo-jet and turbo-prop engines
US2907171A (en) * 1954-02-15 1959-10-06 Lysholm Alf Combustion chamber inlet for thermal power plants
FR998079A (en) * 1958-08-22 1952-01-14 Snecma Device for the entry of air into the primary zone of a turbo-machine combustion chamber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0845639A1 (en) * 1996-11-29 1998-06-03 Abb Research Ltd. Combustor

Also Published As

Publication number Publication date
BE551418A (en)
FR1135017A (en) 1957-04-23
US3082603A (en) 1963-03-26

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