GB872291A - Improvements in or relating to fuel systems for aircraft gas turbine engines - Google Patents
Improvements in or relating to fuel systems for aircraft gas turbine enginesInfo
- Publication number
- GB872291A GB872291A GB1914656A GB1914656A GB872291A GB 872291 A GB872291 A GB 872291A GB 1914656 A GB1914656 A GB 1914656A GB 1914656 A GB1914656 A GB 1914656A GB 872291 A GB872291 A GB 872291A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pressure
- piston
- valve
- nacelle
- burner fuel
- 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
- 230000001419 dependent effect Effects 0.000 abstract 4
- 239000002775 capsule Substances 0.000 abstract 2
- 208000034888 Needle issue Diseases 0.000 abstract 1
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification Methods 0.000 abstract 1
- 238000005192 partition Methods 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWERÂ PLANTSÂ OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Turbines (AREA)
Abstract
872,291. Fluid-pressure servomotor-control systems. BRISTOL SIDDELEY ENGINES Ltd. Sept. 20, 1957 [June 20, 1956], No. 19146/56. Class 135. [Also in Group XXVI] In air-fuel ratio control means for aircraft gas turbine engines, valve 15 controlling burner fuel pressure is actuated by two opposing forces dependent on burner fuel and compressor delivery pressure, of which one is dependent on only a proportion of its determining pressure, the proportion varying with nacelle pressure so that burner fuel pressure varies inversely with nacelle pressure, and by a third force dependent on nacelle pressure whereby burner fuel pressure varies directly with nacelle pressure. The delivery of a pump 10, e.g. as described in Specification 577,016, supplying fuel via a pilot's throttle 11 to the burners 12, is increased when a nozzle 15a is closed by a hinged valve 14 acted upon by a piston 18 responsive to compressor discharge pressure at 18a and by an oppositely acting piston 16 responsive to a proportion of the burner fuel pressure via pipe 19 and restriction 20, the proportion being determined by a needle leak-off valve 22 which closes when pump delivery pressure acting on piston 23 increases, the pump delivery pressure being proportional to the nacelle pressure. A dashpot 31 prevents quick opening of valve 22 on decrease of pressure in pipe 23a due to sudden opening of the throttle 11. The lefthand end of lever 14 extends through a partition 13 into a chamber where nacelle pressure, i.e. air intake pressure dependent on aircraft speed and barometric pressure acts on the top of piston 18 and on a barometric capsule 17 of effective area greater than that of piston 18 so that the capsule and piston close valve 15 with increase in nacelle pressure. In a modification, the burner fuel pressure acts wholly on piston 16 and compressor delivery pressure, similarly modified by valve 22, acts on piston 18, except that valve 22 opens with increase in pump delivery.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1914656A GB872291A (en) | 1956-06-20 | 1956-06-20 | Improvements in or relating to fuel systems for aircraft gas turbine engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1914656A GB872291A (en) | 1956-06-20 | 1956-06-20 | Improvements in or relating to fuel systems for aircraft gas turbine engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB872291A true GB872291A (en) | 1961-07-05 |
Family
ID=10124514
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1914656A Expired GB872291A (en) | 1956-06-20 | 1956-06-20 | Improvements in or relating to fuel systems for aircraft gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB872291A (en) |
-
1956
- 1956-06-20 GB GB1914656A patent/GB872291A/en not_active Expired
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