GB1244553A - Fuel controls for gas turbine engines - Google Patents
Fuel controls for gas turbine enginesInfo
- Publication number
- GB1244553A GB1244553A GB02673/69A GB1267369A GB1244553A GB 1244553 A GB1244553 A GB 1244553A GB 02673/69 A GB02673/69 A GB 02673/69A GB 1267369 A GB1267369 A GB 1267369A GB 1244553 A GB1244553 A GB 1244553A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pressure
- engine
- linkage
- fuel
- discharge pressure
- 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 title abstract 9
- 230000001105 regulatory effect Effects 0.000 abstract 3
- 230000001419 dependent effect Effects 0.000 abstract 1
Classifications
-
- B60K35/60—
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/32—Control of fuel supply characterised by throttling of fuel
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Positive-Displacement Pumps (AREA)
- High-Pressure Fuel Injection Pump Control (AREA)
- Control Of The Air-Fuel Ratio Of Carburetors (AREA)
Abstract
1,244,553. 553. Gas turbine engine fuel systems. UNITED AIRCRAFT CORP. March 11, 1969 [March 29, 1968] , No.12673/69. Heading F1G. A gas turbine engine fuel control comprises fuel metering means, regulating means responsive to a number of engine operating variables for regulating the fuel metering means, sensing means for sensing the pressure of the engine working medium, and means responsive to the sensing means solely when the pressure exceeds a predetermined value for positioning the fuel metering means independently of the regulating means at a velocity dependent on the magnitude by which the pressure of the working medium exceeds the predetermined value. A pump 18 supplies fuel to the engine via a throttle valve 46 having a servopiston 56 controlled by a pilot valve 48. A computer 32 applies a signal force indicative of the ratio of the rate of fuel flow to the compressor discharge pressure and influenced also by the engine intake temperature and pressure and engine speed to a multiplication linkage 40, 42, 44 connected to the pilot valve 48. A signal indicative of the compressor discharge pressure is fed to the multiplication linkage by varying the position of roller 42, whereby the pilot valve is positioned in accordance with the product of the two signals, i. e. the rate of fuel flow. Feedback is applied by a spring 50. The compressor discharge pressure signal is obtained by applying the compresor discharge pressure via a line 26 to a bellows 78, an evacuated bellows 76 connecting the pressure to an absolute value. The bellows operate a pivoted flapper 84 for differentially throttling leak-off nozzles 90, 92 located downstream of respective restrictors 98, 100 connected to the discharge side of pump 18, whereby the pressures applied to opposite sides of a servopiston 110 are correspondingly differentially varied. The piston 110 moves the roller 42 via linkage 112, 114. Feedback is applied through linkage 116 and spring 118. A further linkage 122 connected to the piston 110 carries an arm 124 which is normally separated from lever 44. If the compressor discharge pressure exceeds a predetermined value, the arm 124 bears against the lever 44 and turns it to bring the pilot valve 48 into a position in which it reduces the opening of the throttle valve 46, whereby the compressor discharge pressure is reduced. The predetermined value is set by a cam 132 which can be adjusted by a manual control 134 which rotates it or by an evacuated bellows 138 which moves it axially. The bellows 138, which senses ambient pressure or altitude, may be replaced by a sensor responsive to the engine inlet temperature. The two signals fed to the multiplication linkage may be transposed.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US71719468A | 1968-03-29 | 1968-03-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1244553A true GB1244553A (en) | 1971-09-02 |
Family
ID=24881078
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB02673/69A Expired GB1244553A (en) | 1968-03-29 | 1969-03-11 | Fuel controls for gas turbine engines |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE1914486C3 (en) |
GB (1) | GB1244553A (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3953967A (en) * | 1975-03-18 | 1976-05-04 | United Technologies Corporation | Servoed throttle valve for fuel controls |
US4300348A (en) * | 1979-04-10 | 1981-11-17 | Lucas Industries Limited | Fuel control system for a gas turbine engine |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2822666A (en) * | 1951-08-31 | 1958-02-11 | United Aircraft Corp | Turbine power plant fuel control utilizing speed, temperature and compressor pressure |
DE1096118B (en) * | 1955-04-13 | 1960-12-29 | Bendix Corp | Fuel control device for regulating the output of gas turbine engines |
US3196613A (en) * | 1963-02-11 | 1965-07-27 | United Aircraft Corp | Fuel control |
-
1969
- 1969-03-11 GB GB02673/69A patent/GB1244553A/en not_active Expired
- 1969-03-21 DE DE1914486A patent/DE1914486C3/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
DE1914486C3 (en) | 1981-05-27 |
DE1914486B2 (en) | 1980-09-11 |
DE1914486A1 (en) | 1969-11-06 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4033112A (en) | Fuel control for gas turbine engine | |
US2538582A (en) | Fuel pump control for gas turbine responsive to intake air pressure and temperature | |
GB757900A (en) | Improvements in or relating to pressure ratio sensitive mechanisms | |
GB1237680A (en) | Flow metering apparatus, particularly for combustion engine fuel control | |
GB1156297A (en) | Pneumatic All Speed Governor | |
GB1250702A (en) | ||
GB1244553A (en) | Fuel controls for gas turbine engines | |
US3273338A (en) | Jet engine shock wave control system including fuel supply and exhaust nozzle regulation | |
GB845269A (en) | Improvements in fuel flow control apparatus for gas turbine engines | |
US2882680A (en) | Fuel supply systems for ram jet engines | |
GB1071242A (en) | Fuel supply apparatus for a gas turbine jet engine | |
GB1184779A (en) | Control for Ducted Fan Engine | |
GB1514166A (en) | Pressure signal generating arrangement for a gas turbine engine fuel control system | |
US3002350A (en) | Fuel control device for combustion engines having means for avoiding compressor stall | |
US3958414A (en) | Control valve arrangement for gas turbine engine fuel supply system | |
US4175383A (en) | Gas turbine engine fuel control system | |
GB1513738A (en) | Fuel control system for a gas turbine engine | |
US3037350A (en) | Ramjet fuel control | |
USRE30653E (en) | Fuel control for gas turbine engine | |
GB888328A (en) | Improvements in fuel systems for aircraft gas turbine engines | |
US3365883A (en) | Gas turbine engine fuel control | |
GB1245175A (en) | Improvements relating to differential pressure regulating valves | |
GB814078A (en) | Improvements relating to fuel control systems for gas turbine engines | |
US2862358A (en) | Mechanisms for producing hydraulic pressure signals | |
GB1342733A (en) |