GB791621A - Improvements in or relating to gas turbine engine fuel systems - Google Patents
Improvements in or relating to gas turbine engine fuel systemsInfo
- Publication number
- GB791621A GB791621A GB3514254A GB3514254A GB791621A GB 791621 A GB791621 A GB 791621A GB 3514254 A GB3514254 A GB 3514254A GB 3514254 A GB3514254 A GB 3514254A GB 791621 A GB791621 A GB 791621A
- Authority
- GB
- United Kingdom
- Prior art keywords
- valve
- restrictor
- pressure
- combustion
- energized
- 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
- 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)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
791,621. Supplying liquid fuel to burners. ROLLS-ROYCE, Ltd. Dec. 1, 1955 [Dec. 3, 1954], No. 35142/54. Addition to 694,322. Class 75(1) [Also in Groups XXVI and XXIX] The pressure sensitive device described with reference to Fig. 2 of the parent Specification which is used to control the throttle of an air turbine driving a fuel pump supplying fuel to a reheat combustion stage before a propelling nozzle so as to maintain a preselected value of the ratio of a pressure at a point in the engine between the compressor delivery and the turbine inlet to a pressure at a point in the engine between the turbine and the propelling nozzle has the chamber 77 placed into direct communication with the point in the engine between the turbine and propelling nozzle during the initiation of the reheat combustion. A by-pass 105 around the restrictor 79 is controlled by a valve 106 operated by a solenoid 107. Opening of the valve 106 increases the load on the diaphragm assembly 72, 73 in the sense of opening of the throttle 50. To improve the control of the piston 51 by the valve 66 a second restrictor 101 is placed at the entrance to the space 53. This limits the flow into or out of the space 53 and so limits the rate of travel of the piston 51. This restrictor also modifies the effects of pressure changes in the space 53 due to transient conditions on the diaphragm and capsule assembly 70, 72, 73. To initiate reheat combustion the solenoid 63 is energized and valve 62 thereby closed. The pressure in duct 58 then rises and opens the valve 50 by acting on piston 51. To ensure rapid opening of the valve 50 on initiation of combustion, the solenoid 104 is energized and valve 103 opened. The restrictor 101 is then by-passed. The solenoids 63, 104, 107 may be energized simultaneously to start the reheat combustion but after initiation of combustion only the solenoids 104, 107 are de-energized. A conduit 108 with a restriction 109 is provided to drain water from the conduit 80.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3514254A GB791621A (en) | 1954-12-03 | 1954-12-03 | Improvements in or relating to gas turbine engine fuel systems |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3514254A GB791621A (en) | 1954-12-03 | 1954-12-03 | Improvements in or relating to gas turbine engine fuel systems |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB791621A true GB791621A (en) | 1958-03-05 |
Family
ID=10374316
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3514254A Expired GB791621A (en) | 1954-12-03 | 1954-12-03 | Improvements in or relating to gas turbine engine fuel systems |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB791621A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1167598B (en) * | 1960-11-24 | 1964-04-09 | Hobson Ltd H M | Fuel supply device for a ramjet engine |
-
1954
- 1954-12-03 GB GB3514254A patent/GB791621A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1167598B (en) * | 1960-11-24 | 1964-04-09 | Hobson Ltd H M | Fuel supply device for a ramjet engine |
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