Improvements in or relating to accumulator devices for aircraft engine fuel systems

664,758. Gas turbine fuel system. ROLLSROYCE, Ltd. Feb. 10, 1950 [Feb. 10, 1949], No. 3735/49. Class 110(iii) [Also in Groups XI, XXVII, XXVIII and XXIX] An accumulator for a gas turbine engine fuel system comprises a closed chamber with a flexible diaphragm arranged to divide the chamber into two s...

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Bibliographic Details
Main Authors SMEDLEY FREDERICK EDWARD SAMUEL, BOWNS DESMOND EDWARD
Format Patent
LanguageEnglish
Published 09.01.1952
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:664,758. Gas turbine fuel system. ROLLSROYCE, Ltd. Feb. 10, 1950 [Feb. 10, 1949], No. 3735/49. Class 110(iii) [Also in Groups XI, XXVII, XXVIII and XXIX] An accumulator for a gas turbine engine fuel system comprises a closed chamber with a flexible diaphragm arranged to divide the chamber into two spaces, one of which is connected to the fuel supply system and the other to a source of pressure gas so that the pressure in the second space is substantially constant and is less than the fuel pressure under normal flying conditions. The accumulator shown comprises two hemispherical parts 10, 11, bolted together by flanges 12. The flanges 12 also grip a flexible diaphragm 27 which can lie against one or other of the hemispherical liners 25 mounted in and spaced from the parts 10, 11. The part 11 is connected through a T-shaped union 14 to the fuel supply line 15 and the part 10 to a point on the gas turbine compressor through a conduit 21. A pair of fixed orifices are mounted in the conduit 21 and these together with a relief valve are arranged so that the gas pressure in the part 10 does not exceed the fuel pressure under normal conditions and remains constant. When the fuel pressure falls for any reason, e.g. negative " g " conditions, the gas pressure from the conduit 21 will force fuel from the accumulator to the feed line 15. A non-return valve is provided to prevent the flow of this fuel back into the tank. The relief valve may be connected by a pipeline to the air space above the fuel in the tank so that if the flexible diaphragm is punctured or leaks no fuel is lost.
Bibliography:Application Number: GB19490003735