GB618486A - Improvements relating to gas-turbine fuel-systems - Google Patents

Abstract

618,486. Liquid-fuel burners. DAVIES, K. R., S.U. CARBURETTOR CO., Ltd., and KENT, R. L. Oct. 22, 1946, No. 31415. [Class 75 (i)] [Also in Group XXVI] A fuel system for a gas-turbine engine comprises the combination with a plurality of fuel injection nozzles of the type in which the effective orifice area increases in response to increases in fuel delivery pressure, of fuel delivery areas providing a plurality of fuel supply sources which volumetrically meter the fuel independently to the nozzles or to small groups of nozzles. The fuel delivery means may comprise a multiple plunger pump as described in Specification 617,578 and each nozzle may be constructed as shown in the Figure. Fuel entering the nozzle through the pipe 12 passes along the body 30 and through ports 42 in the abutment 40 of an evacuated resilient capsule 39, held by a spring 41 against an internal shoulder of the body 30, and carried by a piston element 38 slidable in a sleeve 37. The fuel flows around the capsule 39, and an increase or decrease in the fuel pressure causes a collapse or expansion of the capsule thereby moving the element 38 to increase or decrease the effective area of the tangential inlets 43 of the swirl chamber 35 through which the fuel passes to the final delivery orifice 36. During starting the element 38 completely closes the ports 43, whilst ports 44 in the sleeve 37 register with ports 45 in the element 38 so that the fuel passes to the interior of the elements 38 to be swirled by helical grooves 47 and to be ejected through an auxiliary nozzle 48.