GB765359A - Improvements in or relating to fuel supply systems - Google Patents

Abstract

765,359. Gas turbine plant. WESTING- HOUSE ELECTRIC INTERNATIONAL CO. July 6, 1954, No. 19748/54. Class 110 (3). [Also in Groups XI and XXIX] A fuel supply system for effecting equal flows of fuel from a pump or other source of fuel under pressure to the atomizing nozzles 24 of an aircraft gas turbine power plant comprises a distributing valve device 22 having a fuel receiving chamber 34 connected at 35 to the pump, a rotary valve 40 adapted to vary the flow areas of ports 37 leading to the nozzles according to the fuel pressure in the chamber 34, and a spring-loaded valve 52 for establishing a control pressure which is also operative on the valve 40, the flow path to each nozzle 24 being provided with a flow equalizing valve 23 responsive to the opposing effects of the pressure of fuel flowing through the respective port 37 and the control pressure. The valve 52 is adjustably loaded by a spring 56, and sets up a back pressure (which is the control pressure) in a passage 59 and in conduits 68 leading to the flow equalizing valves 23. The latter each comprises two chambers 65, 67 separated by a diaphragm 64 connected to a slide valve 71 controlling a port 72 leading to the respective nozzle 24. The chambers 67 are open to the common control pressure and the chambers 65 to the fuel pressures at the respective ports 37. The valve 40 has ports 41 co-operating with the ports 37 and has an axial shaft 42 connected by a linkage 46 to a spring-loaded diaphragm 43 movable between adjustable stops 47, 48. One side of the diaphragm is open to the pressure in the receiving chamber 34 and the other to the control pressure in the conduits 68. Reference has been directed by the Comptroller to Specification 735,845, [Group XXIX].