GB751013A - Improvements in combustion devices particularly applicable to aircraft jet propulsion units - Google Patents

Improvements in combustion devices particularly applicable to aircraft jet propulsion units

Info

Publication number
GB751013A
GB751013A GB25628/53A GB2562853A GB751013A GB 751013 A GB751013 A GB 751013A GB 25628/53 A GB25628/53 A GB 25628/53A GB 2562853 A GB2562853 A GB 2562853A GB 751013 A GB751013 A GB 751013A
Authority
GB
United Kingdom
Prior art keywords
fuel
air
injector
gas
ring
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
GB25628/53A
Inventor
Gilbert Racine
Benjamin Salmon
Jean Henri Bertin
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 GB751013A publication Critical patent/GB751013A/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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/24—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants of the fluid-screen type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D1/00—Burners for combustion of pulverulent 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
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Abstract

751,013. Generating combustion products under pressure. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Sept. 16, 1953 [Sept. 20, 1952; June 27, 1953], No. 25628/53. Class 51(1). In combustion equipment, for example for reheating the exhaust gases of a jet propulsion engine or for reheating the gases between stages of a gas turbine engine, in which fuel is to be burned in a high velocity stream of combustion supporting gas, nozzle means open into the stream at a substantial angle to the direction of flow thereof for forming a screen-like jet or a number of separate jets transverse to the main stream. The nozzle means are supplied with air or other gas under pressure into which fuel has been injected and the jets form a sheltered zone in which combustion can occur. In Fig. 1 a hollow aerofoil section ring 4 formed with a continuous slot 8 is disposed around the fuel injector 1 and is connected to a source of air or gas under pressure to which fuel has been added. The air and fuel mixture issuing through the slot 8 forms a bowl-shaped screen as indicated by the arrows f and a turbulent zone f 1 forms downstream thereof. The ring 4 is secured to the injector 1 by means of radial struts 5. In Fig. 2 the gaseous screen f is formed by means of a hollow member 4 disposed upstream of the injector 1, the injector discharging in an upstream direction. In a reheat system of a jet propulsion engine, fuel injectors are disposed annularly in the jet pipe and each is associated with a hollow ring as shown in Fig. 1, the rings being interconnected by a manifold. In Fig. 4 a hollow ring 4 is disposed downstream of the injector 1, the ring being formed with a continuous slot 8 on its inner surface. Air or gas is supplied to the ring through the duct 6 and fuel is injected into the duct at la. The air and fuel issues through the slot 8 to form a gaseous baffle as indicated at f. In Fig. 5 gas discharge slots 8 are formed in the hollow radial arms 10 which are connected centrally to a hollow body 11 supplied with air or gas under pressure through a duct 6. Fuel is supplied by injector 1a in the duct 6 and further fuel may be supplied by injectors 1. The slots 8 do not extend right to the wall of the chamber 3 so as to permit an insulating sheath of gas 12 at relatively low temperature to flow along the wall. In the exhaust reheat combustion equipment shown in Fig. 7 air or gas under pressure mixed with fuel issues through orifices 8, or through an annular slot in the inner cone 24. Specification 751,098 is referred to.
GB25628/53A 1953-06-27 1953-09-16 Improvements in combustion devices particularly applicable to aircraft jet propulsion units Expired GB751013A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1063505T 1953-06-27
FR270653X 1953-06-27

Publications (1)

Publication Number Publication Date
GB751013A true GB751013A (en) 1956-06-27

Family

ID=26214381

Family Applications (2)

Application Number Title Priority Date Filing Date
GB16800/55A Expired GB751098A (en) 1953-06-27 1953-09-16 Improvements in combustion devices particularly applicable to aircraft jet propulsion units
GB25628/53A Expired GB751013A (en) 1953-06-27 1953-09-16 Improvements in combustion devices particularly applicable to aircraft jet propulsion units

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GB16800/55A Expired GB751098A (en) 1953-06-27 1953-09-16 Improvements in combustion devices particularly applicable to aircraft jet propulsion units

Country Status (5)

Country Link
CH (1) CH323717A (en)
DE (1) DE1049640B (en)
FR (1) FR1063505A (en)
GB (2) GB751098A (en)
NL (1) NL105199C (en)

Cited By (6)

* 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
US3455108A (en) * 1966-02-28 1969-07-15 Technology Uk Combustion devices
US4137712A (en) * 1976-07-06 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Fluidic combustion control of a solid fuel ramjet
EP0979974A2 (en) * 1998-08-11 2000-02-16 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
US20110219776A1 (en) * 2010-03-15 2011-09-15 General Electric Company Aerodynamic flame stabilizer
CN113551262A (en) * 2021-07-19 2021-10-26 南昌航空大学 Take extension board flame holder of crescent sand dune profile

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1084980B (en) * 1954-08-03 1960-07-07 Snecma Recoil drive
US2948117A (en) * 1956-10-01 1960-08-09 Gen Electric Afterburner flameholder
DE1138588B (en) * 1960-03-01 1962-10-25 Entwicklungsbau Pirna Veb Annular combustion chamber with a rotating fuel injection device, especially for small gas turbines
DE1301338B (en) * 1963-08-24 1969-08-21 Hans Dipl Ing Device for the afterburning of exhaust gases from internal combustion engines
US5685140A (en) * 1995-06-21 1997-11-11 United Technologies Corporation Method for distributing fuel within an augmentor

Cited By (8)

* 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
US3455108A (en) * 1966-02-28 1969-07-15 Technology Uk Combustion devices
US4137712A (en) * 1976-07-06 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Fluidic combustion control of a solid fuel ramjet
EP0979974A2 (en) * 1998-08-11 2000-02-16 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
EP0979974A3 (en) * 1998-08-11 2002-06-05 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
US20110219776A1 (en) * 2010-03-15 2011-09-15 General Electric Company Aerodynamic flame stabilizer
CN113551262A (en) * 2021-07-19 2021-10-26 南昌航空大学 Take extension board flame holder of crescent sand dune profile
CN113551262B (en) * 2021-07-19 2022-06-14 南昌航空大学 Take extension board flame holder of crescent sand dune profile

Also Published As

Publication number Publication date
NL105199C (en)
DE1049640B (en) 1959-01-29
FR1063505A (en) 1954-05-04
CH323717A (en) 1957-08-15
GB751098A (en) 1956-06-27

Similar Documents

Publication Publication Date Title
US2520388A (en) Apparatus for supporting combustion in fast-moving air streams
GB780493A (en) Improvements relating to combustion equipment for gas-turbine engines
GB1180524A (en) Gas Turbine Jet Engine of the By-Pass Type
GB1273017A (en) Improvements in or relating to burners for reheat combustion chambers
GB691068A (en) Fuel burning means for a gaseous-fluid propulsion jet
GB751013A (en) Improvements in combustion devices particularly applicable to aircraft jet propulsion units
GB1451354A (en) Aerodynamic flame holder
GB871842A (en) Improvements in or relating to gas turbine engines
GB1019050A (en) Aircraft-propulsive combustion ducts,such as ramjet engines and turbojet afterburners
US2951341A (en) Fuel injection system for an aircraft engine
GB757332A (en) Liquid fuel combustion chambers for jet-propulsion, engines, gas turbines, or other purposes
GB774059A (en) Improvements in or relating to combined gas turbine plant and ram-jet units
GB719301A (en) Improvements relating to gas turbine engines
GB887829A (en) Improvements relating to flame tubes for combustion systems
GB1399851A (en) Combustion arrangements particularly applicable to the reheat of jet propulsion units
GB811745A (en) Improvements relating to combustion chambers for gas-turbine or jet-propulsion devices and the method of operating the same
GB872600A (en) Improvements in combustion ducts
GB1397296A (en) Combustion apparatus especially for gas turbine engines
GB906865A (en) Improvements in or relating to combustion equipment
GB761167A (en) Flame spreading device for combustion systems
GB933775A (en) Improvements in combustion devices for gas turbine jet engines, applicable especially to reheat
GB702752A (en) Improvements relating to combustion equipment of gas turbine engines
GB811892A (en) Improvements in combustion devices for continuous-flow internal-combustion machines
GB836058A (en) Improvements in flame spreading devices for combustion systems
GB774704A (en) Improvements relating to combustion equipment for gas-turbine engines