GB1078900A – Gas turbine engine fuel system
– Google Patents
GB1078900A – Gas turbine engine fuel system
– Google Patents
Gas turbine engine fuel system
Info
Publication number
GB1078900A
GB1078900A
GB18682/66A
GB1868266A
GB1078900A
GB 1078900 A
GB1078900 A
GB 1078900A
GB 18682/66 A
GB18682/66 A
GB 18682/66A
GB 1868266 A
GB1868266 A
GB 1868266A
GB 1078900 A
GB1078900 A
GB 1078900A
Authority
GB
United Kingdom
Prior art keywords
fuel
filter
valve
conduit
cylinder
Prior art date
1965-05-04
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
GB18682/66A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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.)
1965-05-04
Filing date
1966-04-28
Publication date
1967-08-09
1966-04-28
Application filed by Motors Liquidation Co
filed
Critical
Motors Liquidation Co
1967-08-09
Publication of GB1078900A
publication
Critical
patent/GB1078900A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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
Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
Y10T137/00—Fluid handling
Y10T137/2496—Self-proportioning or correlating systems
Y10T137/2559—Self-controlled branched flow systems
Y10T137/265—Plural outflows
Y10T137/2663—Pressure responsive
Abstract
1,078,900. Fuel supply system. GENERAL MOTORS CORPORATION. April 28, 1966 [May 4, 1965], No. 18682/66. Heading F4T. [Also in Division F1] A gas turbine engine fuel system for supplying fuel to duplex fuel nozzles in an engine 13 via primary and secondary fuel manifolds 11 and 12 comprises a distributing valve 8 fed from a control 7, said valve 8 being shown in a condi tion prior to ignition of the engine. On ignition fuel from a filter 23 enters a cylinder within valve 8 and flows from this cylinder through a line 49 to a portion of a bore 31 in the valve 8 defined by lands 42 and 43. From an enlarged portion 38 of the bore this fuel is fed via conduit 50 to primary manifold 11. Increasing fuel pressure acts on the left-hand side of a piston 37 within cylinder 33 to overcome the loading of a spring 46. A valve spool 34 on which are mounted the lands 42 and 43 and a further land 45 is connected with piston 37 via a stem 35, and movement of the piston causes land 42 to gradually throttle the inlet to conduit 50. Simultaneously land 45 which is provided with converging notches 53 moves to the right and provides communication between enlarged portions 39 and 41 of the valve bore 31, thereby allowing fuel from filter 23 to pass to conduit 51 connected with secondary manifold 12. Ultimately the flow to primary manifold 11 will be cut off -and the main fuel flow supplied through secondary manifold 12. The main fuel flow passes directly through filter 23 cleansing filter element 26 and also cleanses an element of a filter 58 in the conduit 51, said filter 58 having entering it a conduit 57 venting cylinder 33.
GB18682/66A
1965-05-04
1966-04-28
Gas turbine engine fuel system
Expired
GB1078900A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
US453059A
US3360199A
(en)
1965-05-04
1965-05-04
Fuel nozzle fuel proportioning system utilizing a fuel pressure responsive valve
Publications (1)
Publication Number
Publication Date
GB1078900A
true
GB1078900A
(en)
1967-08-09
Family
ID=23799053
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB18682/66A
Expired
GB1078900A
(en)
1965-05-04
1966-04-28
Gas turbine engine fuel system
Country Status (2)
Country
Link
US
(1)
US3360199A
(en)
GB
(1)
GB1078900A
(en)
Cited By (1)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2206159A
(en)
*
1987-06-25
1988-12-29
Gen Electric
Dual manifold fuel supply system for gas turbine engines
Families Citing this family (10)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB1110249A
(en)
*
1967-01-27
1968-04-18
Rolls Royce
Filter device
US3593736A
(en)
*
1969-05-19
1971-07-20
Chandler Evans Inc
Slug pump and pressurizing valve for fuel control system
US3618777A
(en)
*
1969-12-15
1971-11-09
Chandler Evans Inc
Low-flow contaminated fuel transfer system for a fuel control
GB1461765A
(en)
*
1972-12-23
1977-01-19
Simms Group Research Dev Ltd
Fuel supply systems for gas turbine engines
US4726396A
(en)
*
1986-10-22
1988-02-23
Ex-Cell-O Corporation
Fluid valve assembly
GB8708595D0
(en)
*
1987-04-10
1987-05-13
Rolls Royce Plc
Gas turbine fuel control system
US5003771A
(en)
*
1988-10-13
1991-04-02
United Technologies Corporation
Fuel distribution valve for a combustion chamber
US5732730A
(en)
*
1995-09-11
1998-03-31
Delavan Inc
Combined check valve and metering valve assembly
US8256445B2
(en)
*
2008-05-22
2012-09-04
Honeywell International Inc.
Pressurizing and pressure regulating valve and fuel supply system employing the same
FR2999653B1
(en)
*
2012-12-18
2018-09-07
Safran Aircraft Engines
FUEL CIRCUIT OF A TURBOMACHINE
Family Cites Families (10)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US550583A
(en)
*
1895-12-03
bbinok-man
US2759549A
(en)
*
1951-08-31
1956-08-21
United Aircraft Corp
Turboprop fuel control
US2737196A
(en)
*
1952-06-04
1956-03-06
Eaton Mfg Co
Flow divider valve
US2979894A
(en)
*
1954-02-15
1961-04-18
Bendix Corp
Fuel feed and power control system for gas turbine engines having a proportional by-pass fluid control
US2910125A
(en)
*
1954-07-14
1959-10-27
United Aircraft Corp
Hydromechanical fuel control for variable-pitch propeller power plant
DE1089219B
(en)
*
1956-03-27
1960-09-15
Messerschmitt Boelkow Blohm
Fuel delivery device for dual-volume fuel nozzles for aircraft turbines
US2927425A
(en)
*
1956-11-07
1960-03-08
Bendix Aviat Corp
Flow control apparatus
US2963082A
(en)
*
1957-04-02
1960-12-06
Gen Electric
Flow divider for fuel system
GB995142A
(en)
*
1961-06-28
1965-06-16
Lucas Industries Ltd
Filters
US3293858A
(en)
*
1965-02-04
1966-12-27
Chandler Evans Inc
Flow division apparatus for fuel supply system
1965
1965-05-04
US
US453059A
patent/US3360199A/en
not_active
Expired – Lifetime
1966
1966-04-28
GB
GB18682/66A
patent/GB1078900A/en
not_active
Expired
Cited By (2)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2206159A
(en)
*
1987-06-25
1988-12-29
Gen Electric
Dual manifold fuel supply system for gas turbine engines
GB2206159B
(en)
*
1987-06-25
1992-02-19
Gen Electric
A gas turbine engine having a dual manifold fuel system.
Also Published As
Publication number
Publication date
US3360199A
(en)
1967-12-26
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