GB1029603A - Improvements in flow control valves - Google Patents
Improvements in flow control valvesInfo
- 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
Links
- 239000000446 fuel Substances 0.000 abstract 22
- 238000002485 combustion reaction Methods 0.000 abstract 5
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
- F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/12—Actuating 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.
Applications Claiming Priority (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)
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)
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 |
-
1964
- 1964-02-27 US US347818A patent/US3270500A/en not_active Expired - Lifetime
-
1965
- 1965-02-23 DE DEG42914A patent/DE1300354B/en not_active Withdrawn
- 1965-02-24 BE BE660204D patent/BE660204A/xx unknown
- 1965-02-25 GB GB8132/65A patent/GB1029603A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
DE1300354B (en) | 1969-07-31 |
US3270500A (en) | 1966-09-06 |
BE660204A (en) | 1965-06-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1056477A (en) | Liquid or gas supply system for a gas turbine engine | |
GB1106597A (en) | Improvements in multi-nozzle fuel delivery system | |
US2543366A (en) | Two-position fuel valve for gasturbine torch igniters | |
GB1034758A (en) | Improvements in pressurizing and drain valves for gas turbine jet engine fuel systems | |
GB1029603A (en) | Improvements in flow control valves | |
GB1114728A (en) | Burner e.g. for a gas turbine engine combustion chamber | |
GB1457171A (en) | Piezoelectric burner igniters and systems | |
US3381896A (en) | System for purging nozzles in dual fuel burners | |
GB1459720A (en) | Fuel control for a gas turbine engine having auxiliary air bleed | |
EP1338774B1 (en) | Fuel injection system for a combustion engine | |
GB1079949A (en) | Engine starter having a burn rate control valve | |
GB1060051A (en) | Improvements in or relating to gas turbine engines | |
US3472480A (en) | Flow control valve | |
US3318091A (en) | Fuel igniter for a jet turbine engine afterburner | |
GB1271940A (en) | Pressure ratio control system for a gas turbine engine | |
GB1076510A (en) | Device for protecting a gas turbine engine compressor against the effects of surging | |
GB1344341A (en) | Afterburner ignition fuel metering unit for a turbojet engine | |
GB1145165A (en) | Flame failure device | |
GB618688A (en) | Improvements in or relating to fuel-supply systems for gas-turbines | |
US2714801A (en) | Variable area nozzle for a gas turbine | |
GB1077291A (en) | Liquid fuel supply system, for example, for gas turbine engines | |
GB1042097A (en) | Improvements in pressurizing and drain valve | |
GB657213A (en) | Improvements in or relating to fuel supply systems for combustion apparatus | |
GB1485412A (en) | Fuel systems for gas turbine engines | |
GB777352A (en) | Improvements in fuel control means for use with a turbojet engine having an afterburner |