GB751098A - 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
GB751098A
GB751098A GB16800/55A GB1680055A GB751098A GB 751098 A GB751098 A GB 751098A GB 16800/55 A GB16800/55 A GB 16800/55A GB 1680055 A GB1680055 A GB 1680055A GB 751098 A GB751098 A GB 751098A
Authority
GB
United Kingdom
Prior art keywords
nozzle
gas
fuel
disposed
gaseous
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
GB16800/55A
Inventor
Gilbert Racine
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB751098A publication Critical patent/GB751098A/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

751,098. Generating combustion products under pressure. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Sept. 16, 1953 [Sept. 20, 1952], No. 16800/55. Divided out of 751,013. Class 51(1). In combustion equipment in which fuel is burnt in a high velocity stream of combustionsupporting gas, means is provided for forming a stabilised combustion zone and comprises a nozzle device located in the gas stream upstream of the point of fuel injection. The nozzle device is adapted to form a gaseous jet transversely of the flow of the gas stream whereby a turbulent zone is created downstream of the gaseous jet. In Fig. 1 a nozzle device 4 is disposed in a duct 3 through which a stream of combustionsupporting gas flows, the device comprising a hollow ring of faired section and having a continuous slot 8 on its outer surface. The nozzle is supplied with gas under pressure through a valve-controlled pipe 6 and issues through the slot 8 to form a bowl-shaped gaseous screen as indicated at f. A fuel injector 1 is supported within the nozzle device 4 by means of radial struts 5, fuel issuing in a downstream direction. The turbulent flow is indicated at f<SP>1</SP>. In Fig. 2 the gaseous screen is formed by gas under pressure issuing through a slot 8 in a hollow faired body 4 disposed on the axis of the duct 3 and the fuel injector 1 is disposed downstream thereof and injects fuel in an upstream direction. In an application of the invention to exhaust reheat equipment of a gas turbine jet propulsion engine, a series of devices as in Fig. 1 are annularly disposed within the exhaust nozzle, the ring-shaped nozzle devices 4 being interconnected by a ring manifold. Air from the engine compressor is supplied to the nozzle devices. Specifications 733,459 [Group IV(b)] and 745,630 [Group XXVI] also are referred to.
GB16800/55A 1953-06-27 1953-09-16 Improvements in combustion devices particularly applicable to aircraft jet propulsion units Expired GB751098A (en)

Applications Claiming Priority (2)

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

Publications (1)

Publication Number Publication Date
GB751098A true GB751098A (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 After (1)

Application Number Title Priority Date Filing Date
GB25628/53A Expired GB751013A (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 (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2948117A (en) * 1956-10-01 1960-08-09 Gen Electric Afterburner flameholder
EP0750164A1 (en) * 1995-06-21 1996-12-27 United Technologies Corporation Method for distributing fuel within an augmentor

Families Citing this family (9)

* 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
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
DE1235670B (en) * 1962-11-06 1967-03-02 Deutsche Forsch Luft Raumfahrt Device for flame stabilization in constant pressure combustion chambers
DE1301338B (en) * 1963-08-24 1969-08-21 Hans Dipl Ing Device for the afterburning of exhaust gases from internal combustion engines
GB1139004A (en) * 1966-02-28 1969-01-08 Mini Of Technology Improvements in or relating to 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
US6125627A (en) * 1998-08-11 2000-10-03 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
CN113551262B (en) * 2021-07-19 2022-06-14 南昌航空大学 Take extension board flame holder of crescent sand dune profile

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2948117A (en) * 1956-10-01 1960-08-09 Gen Electric Afterburner flameholder
EP0750164A1 (en) * 1995-06-21 1996-12-27 United Technologies Corporation Method for distributing fuel within an augmentor

Also Published As

Publication number Publication date
FR1063505A (en) 1954-05-04
GB751013A (en) 1956-06-27
CH323717A (en) 1957-08-15
DE1049640B (en) 1959-01-29
NL105199C (en)

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