GB659917A - Improvements in fuel supply systems for aircraft engines - Google Patents
Improvements in fuel supply systems for aircraft enginesInfo
- Publication number
- GB659917A GB659917A GB718249A GB718249A GB659917A GB 659917 A GB659917 A GB 659917A GB 718249 A GB718249 A GB 718249A GB 718249 A GB718249 A GB 718249A GB 659917 A GB659917 A GB 659917A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pressure
- boost
- valve
- needle
- metering orifice
- 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
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D9/00—Controlling engines by throttling air or fuel-and-air induction conduits or exhaust conduits
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D2700/00—Mechanical control of speed or power of a single cylinder piston engine
- F02D2700/02—Controlling by changing the air or fuel supply
- F02D2700/0217—Controlling by changing the air or fuel supply for mixture compressing engines using liquid fuel
- F02D2700/022—Controlling the air or the mixture supply as well as the fuel supply
- F02D2700/0223—Engines with fuel injection
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
659,917. Regulating; spray carburetters. HOBSON, Ltd., H. M., and GREENLAND, L. S. March 16, 1949, No. 7182. [Classes 7(iii) and 7(vi)] [Also in Group XXIX] In an aircraft engine fuel supply system of the type in which fuel is delivered through a metering orifice whose area is varied by a variable datum boost control device as a function of boost pressure, and in which the pressure across the orifice is maintained as a function of engine speed, the metering orifice is defined by two relatively movable members, one of which is arranged to be moved manually on operation of a pilot's lever to change the selected boost, and the other is adjusted by means responsive to induction pressure and temperature, and exhaust back-pressure, i.e. atmospheric pressure, and the boost control device includes a resetting piston which adjusts the member coupled to the pilot's lever to correct the fuel flow in accordance with the reduction in boost pressure above full-throttle height. Fuel is delivered bv a pump 1 to the metering orifice defined by a sleeve 3 and a needle 4 whence it passes through a passage 5 to a discharge point at the supercharger intake incorporating a regulating valve 6. The valve 6 is actuated by a diaphragm 15 loaded at its upper side by pressure at the inlet to an engine-driven impeller 11 which discharges into the conduit 2 feeding the metering orifice whereby the pressure across the orifice is related to engine speed. The engine throttle valve 29 is actuated in the idling range by an eccentric 26 on a pilot's control shaft 25 and at other times by a servopiston 28 controlled by a piston valve 48 actuated by a bellows 42 subjected to boost pressure and damped by liquid 51. The datum is varied by a floating lever 39 linked to the shaft 25, to the resetting piston 45 and to the bellows and the sleeve 3. The needle 4 is actuated through a lever 56 by a capsule 57 responsive to temperature in the induction pipe 158 and by a diaphragm 59 exposed on its upper side to atmospheric pressure and on its lower side to boost pressure. The arrangement is such that at idling boosts, when no adjustment of the metering orifice in accordance with exhaust back-pressure is required, the diaphragm 59 will have depressed the needle 4 to such an extent that a flange 54 on the needle will have been brought into contact with a stop 61. During operation below full-throttle height, the metering sleeve 3 is set according to the selected pressure, but above that height, i.e. when the servopiston 28 has reached the limit of its travel, the sleeve is adjusted by the resetting piston 45 which is also controlled by the valve 48 but which, below fullthrottle height, is spring-urged against a stop 47. An adjustable needle 64 in a passage byepassing the metering orifice controls the fuel flow for slow-running. A mixture control valve 36 linked to the shaft 25 is open below cruising boost to weaken the mixture, but is closed above that boost. Specifications 429,682, 567,106, [Group XXIX], 567,239 and 585,275 are referred to.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB718249A GB659917A (en) | 1949-03-16 | 1949-03-16 | Improvements in fuel supply systems for aircraft engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB718249A GB659917A (en) | 1949-03-16 | 1949-03-16 | Improvements in fuel supply systems for aircraft engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB659917A true GB659917A (en) | 1951-10-31 |
Family
ID=9828183
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB718249A Expired GB659917A (en) | 1949-03-16 | 1949-03-16 | Improvements in fuel supply systems for aircraft engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB659917A (en) |
-
1949
- 1949-03-16 GB GB718249A patent/GB659917A/en not_active Expired
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