GB662862A - Improvements in or relating to gas turbine engine fuel systems - Google Patents
Improvements in or relating to gas turbine engine fuel systemsInfo
- Publication number
- GB662862A GB662862A GB115449A GB115449A GB662862A GB 662862 A GB662862 A GB 662862A GB 115449 A GB115449 A GB 115449A GB 115449 A GB115449 A GB 115449A GB 662862 A GB662862 A GB 662862A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pipe
- diaphragms
- flow
- branch
- control
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
662,862. Gas turbine plant. ROLLSROYCE, Ltd. March 7, 1950 [Jan. 14, 1949], No. 1154/49. Class 110(iii) [Also in Group XI] In a gas turbine fuel system having a main fuel delivery pipe connected to a pair of injectors through a pair of branch pipes, each branch pipe has a flow constrictor connected to pressure sensitive means so that the load on the latter is proportional to the fuel flow in the branch pipe and the pressure sensitive means is connected to a flow control valve means in one or both branch pipes so as to maintain the relationship between the respective fuel flows. In the arrangement shown fuel is supplied from a tank 17 by an engine driven pump 18 to two reheat burners 16 through a pipe 20 and two branch pipes 22. Each branch pipe contains a flow constrictor in the form of a venturi 23 and the pressures upstream and at the throats of the venturis are transmitted to the opposite sides of a flexible diaphragms 28 through pipes 29, 30. The two diaphragms 28 are connected together through a rod 31 which actuates two valves 24 so that an increase in flow in a branch pipe causes the valve 24 in that pipe to close and the valve in the other pipe to open. In a modification, the two diaphragms are replaced by a single diaphragm which is loaded on one side by the pressure at the throat of one venturi and on the other by the pressure at the throat of the other venturi. This diaphragm is used to control a single valve in one of the branch pipes. In the first arrangement described, the pressure may be taken downstream instead of upstream of the venturi. The diaphragms may be replaced by equivalent piston and cylinder or capsule devices. The arrangement may be extended to control the flow to more than two injectors by allocating one branch pipe as a master control pipe and providing a control means as described for each of the remaining branch pipes. In effect this arrangement comprises a number of pairs of branch pipes of which one pipe of each pair is the master control pipe. The apparatus may be used to control the fuel flows in a selected ratio to each other by selecting fuel flow restrictors having different characteristics in pipes of the same size, by altering the effective areas of the diaphragms or by connecting the diaphragms through a pivoted lever.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB115449A GB662862A (en) | 1949-01-14 | 1949-01-14 | Improvements in or relating to gas turbine engine fuel systems |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB115449A GB662862A (en) | 1949-01-14 | 1949-01-14 | Improvements in or relating to gas turbine engine fuel systems |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB662862A true GB662862A (en) | 1951-12-12 |
Family
ID=9717119
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB115449A Expired GB662862A (en) | 1949-01-14 | 1949-01-14 | Improvements in or relating to gas turbine engine fuel systems |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB662862A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1048091B (en) * | 1954-08-04 | 1958-12-31 | Josef Szydlowski | Method for controlling the acceleration of jet engines independently of the speed at which the control lever is operated |
| US2916876A (en) * | 1954-06-28 | 1959-12-15 | Rolls Royce | Reheat fuel-system for gas-turbine engine |
-
1949
- 1949-01-14 GB GB115449A patent/GB662862A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2916876A (en) * | 1954-06-28 | 1959-12-15 | Rolls Royce | Reheat fuel-system for gas-turbine engine |
| DE1048091B (en) * | 1954-08-04 | 1958-12-31 | Josef Szydlowski | Method for controlling the acceleration of jet engines independently of the speed at which the control lever is operated |
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