GB1029603A - Improvements in flow control valves - Google Patents

Improvements in flow control valves

Info

Publication number
GB1029603A
GB1029603A GB8132/65A GB813265A GB1029603A GB 1029603 A GB1029603 A GB 1029603A GB 8132/65 A GB8132/65 A GB 8132/65A GB 813265 A GB813265 A GB 813265A GB 1029603 A GB1029603 A GB 1029603A
Authority
GB
United Kingdom
Prior art keywords
line
fuel
reheat
valve
chamber
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
GB8132/65A
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
Priority to US347818A priority Critical patent/US3270500A/en
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB1029603A publication Critical patent/GB1029603A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K3/00Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16KVALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K31/00Actuating devices; Operating means; Releasing devices
    • F16K31/12Actuating devices; Operating means; Releasing devices actuated by fluid

Abstract

1,029,603. Valves. GENERAL ELECTRIC CO. Feb. 25, 1965 [Feb. 27, 1964], No. 8132/65. Heading F2V. [Also in Division F1] The invention relates to a reheat fuel control of a gas turbine jet engine and particularly to a flow control valve in the fuel supply line of a reheat pilot burner system. In the gas turbine jet engine of Fig. 1 (not shown) fuel passes through line 20 to the burners 19 of the main combustion equipment, Fuel may also be supplied from the supply 27 to the reheat burner nozzles 30 by way of pump 35, reheat fuel control 32 and line 30. When reheat is switched on, fuel under pressure is directed by valve 34 through line 38 to the pilot burner valve 39 which causes fuel to be discharged through line 41 to the pilot burner nozzle 42 in the reheat combustion section where the fuel is ignited thus providing a pilot flame for the fuel supplied to the main reheat fuel burners 30. The pilot burner valve 39 is shown in Fig. 2 and comprises a housing 46 which forms a cavity 50 in which is disposed a piston 51. The housing 46 is formed with an inlet 47 to which is connected a line 40 leading from the fuel line 20 to the main combustion section 14, an inlet 48 to which is connected the fuel line 38 leading from the valve 34 of the reheat fuel system, and an outlet 49 which leads through line 41 to the reheat pilot burner 42. In normal engine operation the valve is disposed as shown in Fig. 2 in which the piston 51 is biased by the spring 57 to the left so that the extension 58 of the piston bears against the valve seat 59 to close off the outlet to line 41. No fuel pressure is applied in line 38 so that the chamber 50c is vented to atmosphere. Fuel pressure in the line 20 is communicated through line 40, filter 55 and restrictor assembly 56 to the chamber 50a at the right-hand side of the piston 51. This fuel passes through the bore 61 in the extension 58 of the piston, through openings 62 to the chamber 50b which is sealed at the valve 59. When reheat is switched on fuel under pressure passes through line 38 to the pilot burner valve 39, through inlet 48 to the compartment 50c at the left-hand side of the piston 51 whereupon the piston moves to the right and fuel in the chamber 50a is forced through the bore 61 and openings 62 into the chamber 50b and from there through the valve 59 which is now open to the line 41 and so to the pilot burner 42 of the reheat combustion equipment. Fuel will also pass from the line 20 (which leads to the main combustion section) through line 40 to the chamber 50a and thus through line 41 to the pilot burner 42 as long as piston 51 is held to the right by fuel pressure in chamber 50c. Fuel will simultaneously flow through line 33 to the reheat fuel control 32, through line 31 to the main reheat burner 30. When reheat is switched off, the chamber 50c is vented to atmosphere through line 38, the piston 51 is moved to the left to the position shown in Fig. 2 and the chamber 50a is re-filled ready for the next reheat operation.
GB8132/65A 1964-02-27 1965-02-25 Improvements in flow control valves Expired GB1029603A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US347818A US3270500A (en) 1964-02-27 1964-02-27 Afterburner fuel control

Publications (1)

Publication Number Publication Date
GB1029603A true GB1029603A (en) 1966-05-18

Family

ID=23365408

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8132/65A Expired GB1029603A (en) 1964-02-27 1965-02-25 Improvements in flow control valves

Country Status (4)

Country Link
US (1) US3270500A (en)
BE (1) BE660204A (en)
DE (1) DE1300354B (en)
GB (1) GB1029603A (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1284287A (en) * 1968-10-10 1972-08-02 Snecma A device for programming the ignition stage of the re-heat combustion in a gas turbine power plant
GB2202904B (en) * 1987-03-23 1991-09-11 Rolls Royce Plc A method and apparatus for evaluating the working line characteristics of a compressor of a gas turbine engine
US4973026A (en) * 1988-08-01 1990-11-27 Saurwein Albert C High pressure water jet cutting nozzle on-off valve
US5020314A (en) * 1989-06-19 1991-06-04 Williams International Corporation Multiple fluid speed systems
EP1909077A1 (en) * 2006-10-02 2008-04-09 Syngeta Participations AG Liquid dispensing device
US9316157B2 (en) * 2012-02-01 2016-04-19 Hamilton Sundstrand Corporation Fuel system for starting an APU using a hybrid pump arrangement
CN103832427B (en) * 2014-03-18 2016-09-14 深圳嘉贸气动器材有限公司 A kind of automobile-used Pneumatic controller

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2640316A (en) * 1949-11-07 1953-06-02 Westinghouse Electric Corp Ignition apparatus for turbojet afterburners
CH290429A (en) * 1949-11-14 1953-04-30 Rolls Royce Post-heating fuel supply device in gas turbine systems.
US2804241A (en) * 1951-09-15 1957-08-27 Gen Motors Corp Flow control meter
US2829489A (en) * 1952-11-15 1958-04-08 United Aircraft Corp Repeating cycle igniter control
DE1045733B (en) * 1954-08-31 1958-12-04 United Aircraft Corp Automatic control system of the flame ignition device for after-burners of turbine jet engines
US3019598A (en) * 1958-07-23 1962-02-06 Gen Motors Corp Afterburner fuel igniter
GB864392A (en) * 1958-11-10 1961-04-06 Rexall Drug Company Ltd Improvements in or relating to dispensing devices for aerosols
US3062005A (en) * 1959-08-26 1962-11-06 Rolls Royce Coordinated variable area nozzle and reheat fuel control for a gas turbine engine
GB928018A (en) * 1960-11-15 1963-06-06 Rolls Royce Reheat apparatus for a gas turbine engine

Also Published As

Publication number Publication date
BE660204A (en) 1965-06-16
DE1300354B (en) 1969-07-31
US3270500A (en) 1966-09-06

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