[go: up one dir, main page]

GB914906A - Burner for hot fuel - Google Patents

Burner for hot fuel

Info

Publication number
GB914906A
GB914906A GB4192259A GB4192259A GB914906A GB 914906 A GB914906 A GB 914906A GB 4192259 A GB4192259 A GB 4192259A GB 4192259 A GB4192259 A GB 4192259A GB 914906 A GB914906 A GB 914906A
Authority
GB
United Kingdom
Prior art keywords
combustion chamber
nozzle
nozzles
wall
discharging
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
GB4192259A
Inventor
Otto Frenzl
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 GB914906A publication Critical patent/GB914906A/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
    • F23R3/60—Support structures; Attaching or mounting 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
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)

Abstract

914,906. Liquid fuel burners. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Dec. 9, 1959 [Dec. 10, 1958], No. 41922/59. Classes 75 (1) and 75 (3). [Also in Group XXVI] A burner for an aircraft engine combustion chamber 1 through which a gaseous flow travels at high speed comprises a divergent nozzle 2 supplied with hot liquid fuel, the length and divergence of the nozzle being such that the fuel is vaporized at least partially by expansion. The nozzle also comprises a convergent portion upstream of the divergent portion. The cross-section of the throat may be regulated by a needle valve 9. The end of the divergent portion is cut away over a semicircular area to allow part of the fuel to enter a recess 5 in the wall of the combustion chamber where it is ignited by a sparking plug 8. The uncut end of the divergent part may be flush with the combustion chamber wall as shown or may project into the chamber. The nozzle may be inclined upstream or directed in countercurrent to the gaseous flow in the combustion chamber. In a modification, Fig. 6 (not shown), the nozzle discharges into a cylindrical pipe 11 which leads to the combustion chamber and the fuel aspirates air into the cylindrical tube 11. The mixture so ignited by a sparking plug in a recess in the wall of the combustion chamber beside a cut-away portion of the end of the cylindrical tube 11. Figs. 7, 8, 9 (not shown) show a ring of nozzles mounted on the outer wall or on the inner wall of an annular post combustion chamber of a turbo-jet engine, the nozzles discharging in a radial direction. Nozzles producing short wide jets alternate with nozzles producing longer jets. Figs. 10, 11, 12 (not shown) show burners according to the invention mounted in alternate arrangement with conventional burners in a ring and discharging into an annular combustion chamber in the direction of the main air flow therein. Each nozzle of the burners according to the invention takes the form of two coaxial cones bounding a space which first decreases and then increases. Fig. 13 (not shown) shows nozzles according to the invention mounted on an aircraft upstream of a ram jet engine and discharging into the external air stream entering the engine. Fig. 14 (not shown) shows nozzles according to the invention mounted in a triangular wing and discharging into the external air flow below the wing.
GB4192259A 1958-12-10 1959-12-09 Burner for hot fuel Expired GB914906A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR781301A FR1217843A (en) 1958-12-10 1958-12-10 Hot fuel combustion or post-combustion burner

Publications (1)

Publication Number Publication Date
GB914906A true GB914906A (en) 1963-01-09

Family

ID=8709116

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4192259A Expired GB914906A (en) 1958-12-10 1959-12-09 Burner for hot fuel

Country Status (2)

Country Link
FR (1) FR1217843A (en)
GB (1) GB914906A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0387532A1 (en) * 1989-03-15 1990-09-19 Asea Brown Boveri Ag Gas turbine combustion chamber
US5193995A (en) * 1987-12-21 1993-03-16 Asea Brown Boveri Ltd. Apparatus for premixing-type combustion of liquid fuel
WO2007099046A1 (en) * 2006-02-28 2007-09-07 Siemens Aktiengesellschaft Gas turbine burner and method of operating a gas turbine burner
FR2996288A1 (en) * 2012-10-01 2014-04-04 Turbomeca DUAL TURBOMACHINE COMBUSTION CHAMBER INJECTOR.
EP3098420A4 (en) * 2014-03-31 2017-03-22 Mitsubishi Heavy Industries, Ltd. Jet engine, flying vehicle, and method for operating jet engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1235670B (en) * 1962-11-06 1967-03-02 Deutsche Forsch Luft Raumfahrt Device for flame stabilization in constant pressure combustion chambers

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5193995A (en) * 1987-12-21 1993-03-16 Asea Brown Boveri Ltd. Apparatus for premixing-type combustion of liquid fuel
EP0387532A1 (en) * 1989-03-15 1990-09-19 Asea Brown Boveri Ag Gas turbine combustion chamber
CH678757A5 (en) * 1989-03-15 1991-10-31 Asea Brown Boveri
US5081844A (en) * 1989-03-15 1992-01-21 Asea Brown Boveri Ltd. Combustion chamber of a gas turbine
JP3077763B2 (en) 1989-03-15 2000-08-14 アセア・ブラウン・ボヴエリ・アクチエンゲゼルシヤフト Gas turbine combustion chamber
WO2007099046A1 (en) * 2006-02-28 2007-09-07 Siemens Aktiengesellschaft Gas turbine burner and method of operating a gas turbine burner
FR2996288A1 (en) * 2012-10-01 2014-04-04 Turbomeca DUAL TURBOMACHINE COMBUSTION CHAMBER INJECTOR.
WO2014053730A3 (en) * 2012-10-01 2014-07-17 Turbomeca Two-circuit injector for a turbine engine combustion chamber
JP2015531448A (en) * 2012-10-01 2015-11-02 ターボメカＴｕｒｂｏｍｅｃａ Two circuit injector for turbine engine combustion chamber
US9927125B2 (en) 2012-10-01 2018-03-27 Turbomeca Two-circuit injector for a turbine engine combustion chamber
EP2904329B1 (en) * 2012-10-01 2019-11-27 Safran Helicopter Engines Two-circuit injector for a turbine engine combustion chamber
EP3098420A4 (en) * 2014-03-31 2017-03-22 Mitsubishi Heavy Industries, Ltd. Jet engine, flying vehicle, and method for operating jet engine
US11203984B2 (en) 2014-03-31 2021-12-21 Mitsubishi Heavy Industries, Ltd. Jet engine, flying object, and method of operating a jet engine

Also Published As

Publication number Publication date
FR1217843A (en) 1960-05-05

Similar Documents

Publication Publication Date Title
US2520388A (en) Apparatus for supporting combustion in fast-moving air streams
US2517015A (en) Combustion chamber with shielded fuel nozzle
US3558251A (en) High tension igniter plugs
GB1421399A (en) Fuel injectors
GB1458066A (en) Gas turbine combustion chambers
US2720753A (en) Combustion apparatus
US2705869A (en) Combustion apparatus
US2735263A (en) charshafian
GB1418736A (en) Igniter assemblies for afterburners of gas turbine engines
GB780493A (en) Improvements relating to combustion equipment for gas-turbine engines
GB1328623A (en) Fuel spray nozzle
US2692480A (en) Supersonic internal circulation combustion chamber, in particular combustion chamber for aircraft jet engines
US2720754A (en) Flameholder for ram jet engine
US3026675A (en) Device for the air intake into the primary zone of a combustion chamber in a turbo-machine
US2982099A (en) Fuel injection arrangement in combustion equipment for gas turbine engines
US3074668A (en) Burner for hot fuel
US5680765A (en) Lean direct wall fuel injection method and devices
GB914906A (en) Burner for hot fuel
US3055178A (en) Ramjet ignition system
US6067790A (en) Lean direct wall fuel injection method and devices
US4203285A (en) Partial swirl augmentor for a turbofan engine
US3046731A (en) Flame stabilization in jet engines
US3355891A (en) Ram jet engine and fuel injection system therefor
US2657532A (en) Liquid fuel atomizer located upstream of a flame stabilizing baffle
GB2143938A (en) Fuel burner for a gas turbine engine