GB808419A - Liquid fuel control means for aircraft engines - Google Patents
Liquid fuel control means for aircraft enginesInfo
- Publication number
- GB808419A GB808419A GB1816455A GB1816455A GB808419A GB 808419 A GB808419 A GB 808419A GB 1816455 A GB1816455 A GB 1816455A GB 1816455 A GB1816455 A GB 1816455A GB 808419 A GB808419 A GB 808419A
- Authority
- GB
- United Kingdom
- Prior art keywords
- throttle
- valve
- passage
- pressure
- bellows
- 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
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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of The Air-Fuel Ratio Of Carburetors (AREA)
Abstract
808,419. Gas turbine plant. LUCAS (INDUSTRIES) Ltd., J. June 25, 1956 [June 23, 1955], No. 18164/55. Class 110 (3). [Also in Group XXIX] A liquid fuel control means for an aircraft jet-propulsion or turbine engine having a barometrically controlled throttle a in series with a manually operable throttle r in a main fuel passage c, comprises a passage v by-passing the throttles between the inlet and outlet of passage c and containing a restricted orifice w, a third throttle 7 connected to the manual throttle, and a servo-control valve 12 actuated in response to the pressure difference across the third throttle or the orifice, for controlling a servo mechanism adjusting the rate of supply of fuel by a pump (not shown) to the combustion chamber of the engine. An evacuated bellows n and a bellows o exposed to atmosphere actuate a hinged valve j controlling a leak-off from a cylinder b supplied with pressure from the by-pass via a restriction h whereby the pressure in chamber b positions the piston and valve a, follow-up between the valves a, being through the spring p. Thus valve a closes the main passage as atmospheric pressure falls with increasing altitude. The bellows 2 actuating a valve 12 controlling the leak off from the spring-loaded side of a piston (not shown) connected to passage 11 and supplied with pressure on the unloaded side and both sides being connected through a throttle, is exposed to the pressure difference across the throttle 7 controlling the end of the by-pass passage in the same way as the manual valve r, to which it is connected at 8, controls the main fuel passage t. If the bellows 2 is connected across the orifice w the valve 7 controls oppositely to valve r. Increase of pressure difference across throttle 7 moves the piston to reduce the delivery from a variable delivery pump, throttles the delivery or opens a valve by-passing the pump. In another embodiment the manual throttle r is placed upstream of the throttle a.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1816455A GB808419A (en) | 1955-06-23 | 1955-06-23 | Liquid fuel control means for aircraft engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1816455A GB808419A (en) | 1955-06-23 | 1955-06-23 | Liquid fuel control means for aircraft engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB808419A true GB808419A (en) | 1959-02-04 |
Family
ID=10107753
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1816455A Expired GB808419A (en) | 1955-06-23 | 1955-06-23 | Liquid fuel control means for aircraft engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB808419A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4011716A (en) * | 1974-05-21 | 1977-03-15 | Lucas Industries Limited | Fuel control system for gas turbine engine |
-
1955
- 1955-06-23 GB GB1816455A patent/GB808419A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4011716A (en) * | 1974-05-21 | 1977-03-15 | Lucas Industries Limited | Fuel control system for gas turbine engine |
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