GB933775A - Improvements in combustion devices for gas turbine jet engines, applicable especially to reheat - Google Patents

Improvements in combustion devices for gas turbine jet engines, applicable especially to reheat

Info

Publication number
GB933775A
GB933775A GB1389560A GB1389560A GB933775A GB 933775 A GB933775 A GB 933775A GB 1389560 A GB1389560 A GB 1389560A GB 1389560 A GB1389560 A GB 1389560A GB 933775 A GB933775 A GB 933775A
Authority
GB
United Kingdom
Prior art keywords
fuel
manifold
manifolds
ring
flame
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
GB1389560A
Inventor
Louis Jules Bauger
Armand Jean-Baptiste Lacroix
Pierre Marcel Phelipon
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 GB933775A publication Critical patent/GB933775A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/222—Fuel flow conduits, e.g. manifolds
    • 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

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

933,775. Generating combustion products under pressure. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. April 20, 1960 [April 21, 1959], No. 13895/60. Class 51(1). In combustion equipment for gas turbine jet propulsion engines particularly reheat equipment thereof, flame-stabilizing rings 5, 6 of V-section are provided and a fuel ring manifold 7, 8 is disposed within each V-section ring, fuel being delivered from orifices 7a in the manifold through openings 5a formed at the angle of the V-section, and further fuel ring manifolds 9, 10 are provided upstream of the flame-stabilizing rings and of such a diameter relative to the flame stabilizer rings that the fuel delivered by them flows in contact with the flame stabilizers. Fuel is supplied to the ring manifolds 7, 8, 9, 10 through inlet portions 3, the inlet portions together with rods 2 serving to support the manifolds and stabilizing rings within the jet pipe 1. The manifolds 7, 8 may be supported within the stabilizing rings 5, 6 by a member 12, as shown in Fig. 7, which permits differential expansion of the two components. Various arrangements of apparatus, having two or three flame stabilizing rings and two or three further ring manifolds upstream thereof are described. In Fig. 13, two fuel ring manifolds 25, 26 are disposed within the flame stabilizing ring 5, one manifold 25 having a low delivery coefficient and the other 26 having a high coefficient, fuel being supplied through the manifold 26 up to a certain altitude and then through the manifold 25. The two manifolds 25, 26 may be disposed one downstream of the other, the downstream manifold injecting fuel with a downstream component of velocity while the upstream manifold injects fuel in an upstream direction.
GB1389560A 1959-04-21 1960-04-20 Improvements in combustion devices for gas turbine jet engines, applicable especially to reheat Expired GB933775A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR792736A FR1232450A (en) 1959-04-21 1959-04-21 Improvements to jet thruster combustion devices, particularly applicable to post-combustion

Publications (1)

Publication Number Publication Date
GB933775A true GB933775A (en) 1963-08-14

Family

ID=8713931

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1389560A Expired GB933775A (en) 1959-04-21 1960-04-20 Improvements in combustion devices for gas turbine jet engines, applicable especially to reheat

Country Status (2)

Country Link
FR (1) FR1232450A (en)
GB (1) GB933775A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112728584A (en) * 2020-11-24 2021-04-30 南京航空航天大学 Flame stabilizer, radial flame stabilizer and combustion chamber

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2193145B1 (en) * 1972-07-21 1976-02-13 Snecma Fr
GB1605162A (en) * 1977-01-21 1982-08-25 Rolls Royce Reheat systems for gas turbine engines
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112728584A (en) * 2020-11-24 2021-04-30 南京航空航天大学 Flame stabilizer, radial flame stabilizer and combustion chamber
CN112728584B (en) * 2020-11-24 2021-12-07 南京航空航天大学 Flame stabilizer, radial flame stabilizer and combustion chamber

Also Published As

Publication number Publication date
FR1232450A (en) 1960-10-07

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