GB1092643A - Improvements to combustion devices for gas turbine jet propulsion engines, applicable more particularly to reheat - Google Patents

Improvements to combustion devices for gas turbine jet propulsion engines, applicable more particularly to reheat

Info

Publication number
GB1092643A
GB1092643A GB2006465A GB2006465A GB1092643A GB 1092643 A GB1092643 A GB 1092643A GB 2006465 A GB2006465 A GB 2006465A GB 2006465 A GB2006465 A GB 2006465A GB 1092643 A GB1092643 A GB 1092643A
Authority
GB
United Kingdom
Prior art keywords
manifold
fuel
secured
ring
gas turbine
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
GB2006465A
Inventor
Rene Leon Constant
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 GB1092643A publication Critical patent/GB1092643A/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
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Abstract

1,092,643. Gas turbine combustion equipment. SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. May 12, 1965 [May 12, 1964], No. 20064/65. Heading F1L. In combustion equipment for gas turbine jet engines comprising V-section flame stabilizing rings each containing a fuel injection manifold from which fuel is discharged in an upstream direction through apertures formed at the point of the V, the fuel injection manifolds are protected wholly or in part from heat radiation downstream therefrom by means of screens disposed downstream of the fuel manifolds but within the flame stabilizing rings. A flame stabilizing ring is indicated at 2 and the fuel injection manifold disposed therein at 1, the fuel manifold being secured to the ring by means of a clip 5 surrounding the manifold and extending into a boss 9 mounted at the point of the V-section, the parts being secured by a bolt 11. A series of arcuate-section shields 12 is secured to the fuel manifold and spaced therefrom by means of rivets. The assembly of shields 12 together forms a ring-shaped shield disposed within the flame stabilizer ring and protecting the fuel manifold from radiation from the combustion zone downstream thereof. Spacers 13 are secured to the fuel manifold adjacent the ends of the shield elements to maintain the shields in spaced relation to the manifold.
GB2006465A 1964-05-12 1965-05-12 Improvements to combustion devices for gas turbine jet propulsion engines, applicable more particularly to reheat Expired GB1092643A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR974179A FR85730E (en) 1964-05-12 1964-05-12 Improvements to jet thruster combustion devices, particularly applicable to post-combustion

Publications (1)

Publication Number Publication Date
GB1092643A true GB1092643A (en) 1967-11-29

Family

ID=8829836

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2006465A Expired GB1092643A (en) 1964-05-12 1965-05-12 Improvements to combustion devices for gas turbine jet propulsion engines, applicable more particularly to reheat

Country Status (3)

Country Link
DE (1) DE1950033U (en)
FR (1) FR85730E (en)
GB (1) GB1092643A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2873408A1 (en) * 2004-07-23 2006-01-27 Snecma Moteurs Sa TURBOREACTOR WITH A PROTECTION SCREEN OF THE FUEL RAMP OF A BURNER RING, THE BURNER RING AND THE PROTECTION SCREEN

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2586792B1 (en) * 1985-09-03 1989-06-16 Snecma CONNECTION DEVICE BETWEEN A BURNER RING OR FLAME HANGER OF COMPOSITE MATERIAL AND A POST-COMBUSTION CHAMBER CHANNEL OF A TURBOREACTOR
US10578021B2 (en) * 2015-06-26 2020-03-03 Delavan Inc Combustion systems

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2873408A1 (en) * 2004-07-23 2006-01-27 Snecma Moteurs Sa TURBOREACTOR WITH A PROTECTION SCREEN OF THE FUEL RAMP OF A BURNER RING, THE BURNER RING AND THE PROTECTION SCREEN
US7574866B2 (en) 2004-07-23 2009-08-18 Snecma Turbo-jet engine with a protective screen of the fuel manifold of a burner ring, the burner ring and the protective screen

Also Published As

Publication number Publication date
DE1950033U (en) 1966-11-17
FR85730E (en) 1965-10-01

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