GB874502A - Improvements in fuel distribution system for jet propulsion engine afterburners - Google Patents

Improvements in fuel distribution system for jet propulsion engine afterburners

Info

Publication number
GB874502A
GB874502A GB1694758A GB1694758A GB874502A GB 874502 A GB874502 A GB 874502A GB 1694758 A GB1694758 A GB 1694758A GB 1694758 A GB1694758 A GB 1694758A GB 874502 A GB874502 A GB 874502A
Authority
GB
United Kingdom
Prior art keywords
fuel
manifolds
flow
groups
shown
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
GB1694758A
Inventor
Milton Howard Shackelford
Walter Stanley Bertaux
Hans Bollenbacher
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to CH7862059A priority Critical patent/CH375176A/en
Publication of GB874502A publication Critical patent/GB874502A/en
Application status is Expired legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/22Fuel supply systems
    • F02C7/228Dividing fuel between various burners

Abstract

874,502. Jet propulsion plant. GENERAL ELECTRIC CO. May 27, 1958, No. 16947/58. Class 110 (3). In a fuel distribution system for jet propulsion afterburners having a series of radially extending spray bars arranged substantially in a plane at right angles to the longitudinal axis of the afterburner combustion zone, and manifolds connecting selected groups of spray bars, fuel control means responsive to engine operating conditions control the quantity of fuel passing to the manifolds and a fuel selector valve positioned in accordance with the engine throttle setting is associated with at least one manifold to control the fuel distribution to that manifold after distribution to the manifolds has been initiated by the fuel control means. The groups of spray bars are brought into operation sequentially and remain in operation until finally all are in operation and complete fuel distribution over the whole combustion zone area is achieved. The fuel spray bars of an afterburner, Fig. 2, are arranged in a number of groups 17, 18, 20, 21, which are connected in pairs to separate fuel supply manifolds 19, 22. It is not essential that the groups 17, 18, 20, 21 overlap as shown. The groups of fuel injectors 17, 18, 20, 21 are represented by triangles 23, 24, in Fig. 3. Fuel supplied by a pump 25 is metered by a control 26 in response to engine operating conditions which, as shown, are compressor discharge pressure and the throttle lever position. In operation, fuel is first supplied by the fuel control through sectors 24 to provide fuel injection in sector patterns and when a predetermined throttle position is reached a fuel selector valve 32 is actuated, and fuel is injected through the additional sectors 23 to provide for uniform distribution throughout the tail-pipe combustion area. In a modification, Fig. 4 (not shown), a flow dividing valve is provided, to divide the fuel flow proportionally between the manifolds 19, 22. To avoid over-rich mixtures at increased fuel flows, the flow-dividing valve may be arranged to vary the proportions supplied to the manifolds as the total fuel flow increases. In another modification, Fig. 5 (not shown), the flow divider valve is used to divide the flow between two fuel injector systems of the kind shown in Fig. 3.
GB1694758A 1959-09-24 1958-05-27 Improvements in fuel distribution system for jet propulsion engine afterburners Expired GB874502A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CH7862059A CH375176A (en) 1959-09-24 1959-09-24 Augmentor on jet engine

Publications (1)

Publication Number Publication Date
GB874502A true GB874502A (en) 1961-08-10

Family

ID=4536602

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1694758A Expired GB874502A (en) 1959-09-24 1958-05-27 Improvements in fuel distribution system for jet propulsion engine afterburners

Country Status (3)

Country Link
CH (1) CH375176A (en)
GB (1) GB874502A (en)
NL (2) NL247184A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2250086A (en) * 1988-10-13 1992-05-27 United Technologies Corp Preventing blow-out in a gas turbine engine combustion chamber
EP0979974A2 (en) * 1998-08-11 2000-02-16 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
EP1475569A1 (en) * 2003-05-08 2004-11-10 General Electric Company Sector staging combustor

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2250086A (en) * 1988-10-13 1992-05-27 United Technologies Corp Preventing blow-out in a gas turbine engine combustion chamber
GB2250086B (en) * 1988-10-13 1992-11-18 United Technologies Corp Method of operating a combustion chamber for a gas turbine engine
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
US6668541B2 (en) 1998-08-11 2003-12-30 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
EP1475569A1 (en) * 2003-05-08 2004-11-10 General Electric Company Sector staging combustor
US6968699B2 (en) 2003-05-08 2005-11-29 General Electric Company Sector staging combustor

Also Published As

Publication number Publication date
NL111223C (en)
NL247184A (en)
CH375176A (en) 1964-02-15

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