GB861530A - Improved gas turbine engine fuel system - Google Patents
Improved gas turbine engine fuel systemInfo
- Publication number
- GB861530A GB861530A GB1503858A GB1503858A GB861530A GB 861530 A GB861530 A GB 861530A GB 1503858 A GB1503858 A GB 1503858A GB 1503858 A GB1503858 A GB 1503858A GB 861530 A GB861530 A GB 861530A
- Authority
- GB
- United Kingdom
- Prior art keywords
- orifice
- size
- lever
- engine
- slot
- 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)
- High-Pressure Fuel Injection Pump Control (AREA)
Abstract
861,530. Gas turbine fuel systems. ROLLSROYCE Ltd. May 11, 1959 [May 10, 1958], No. 15038/58. Class 110 (3). A gas turbine fuel system comprises a metering orifice through which pressurized fuel may flow to the engine, first orifice adjustment means for varying the size of the orifice in accordance with engine rotational speed, second orifice adjustment means for varying the size of the orifice in accordance with another engine variable and limit means for limiting the maximum size of the orifice, the arrangement being such that, when the second orifice adjustment means has increased the size of the orifice to a predetermined extent, the limit means opposes further increase in the orifice size by the second orifice adjustment mass and simultaneously alters the operation of the first orifice adjustment means so that the engine rotational speed at which the latter restricts the size of the orifice is increased. The fuel system has an orifice through which the fuel is metered which comprises a variable width rectangular slot 26 and a relatively movable triangular slot 27. The slot 26 is formed between a fixed edge 28 and a relatively movable edge 29 carried by a frame 30 actuated by engine-driven governor weights 34 through a collar 32 and shaft 31. The slot 27 is actuated by a bellows 27a which is subjected to an air pressure proportional to P 1 F(P 2 /P 1 ), where P 1 and P 2 are the compressor intake and outlet pressures and F any desired function. To retain the maximum fuel flow and prevent overfuelling of the engine, a lever 105 mounted on a point 106 has its forward end arranged so as to be in the path of travel of the plate 24. The other end of the lever 105 is connected through a link 108 and a second pivoted lever 107 to the frame 30. When the plate 24 abuts the lever 105, the lever 105 applies an additional load to the frame 30 and so to the governor which has to be overcome before the governor can reduce the width of the slot 26 and so reduce the fuel flow. A practical form of the orifice and control gear is also described. Specification 850,477 is referred to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1503858A GB861530A (en) | 1958-05-10 | 1958-05-10 | Improved gas turbine engine fuel system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1503858A GB861530A (en) | 1958-05-10 | 1958-05-10 | Improved gas turbine engine fuel system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB861530A true GB861530A (en) | 1961-02-22 |
Family
ID=10051954
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1503858A Expired GB861530A (en) | 1958-05-10 | 1958-05-10 | Improved gas turbine engine fuel system |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB861530A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2576360A1 (en) * | 1985-01-24 | 1986-07-25 | Snecma | ASSAY DEVICE, IN PARTICULAR FOR THE FUEL OF A TURBOMACHINE |
-
1958
- 1958-05-10 GB GB1503858A patent/GB861530A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2576360A1 (en) * | 1985-01-24 | 1986-07-25 | Snecma | ASSAY DEVICE, IN PARTICULAR FOR THE FUEL OF A TURBOMACHINE |
| EP0190963A1 (en) * | 1985-01-24 | 1986-08-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Fuel-metering valve for a turbo machine |
| US4745739A (en) * | 1985-01-24 | 1988-05-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Fuel metering device for a turbojet engine |
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