GB687022A - Improvements in apparatus for supplying liquid fuel to continuous combustion turbineengines - Google Patents

Abstract

687,022. Gas turbine plant. DOWTY EQUIPMENT, Ltd. June 18, 1951 [Sept. 11, 1950], No. 22338/50. Class 110(iii) [Also in Group XXIX] In a fuel system for a continuous combustion turbine engine in which the fuel flow is controlled by venting one side of a pressure balanced device which controls either the setting of a variablestroke fuel pump or the effectiveness of a by-pass associated with a pump of fixed displacement, the vent 12 is adjusted by a lever 16 which is pivoted at 17 and upon which act two opposed loadings, one of which is a measure of the air flow to the engine and the other a measure of the fuel flow. The arrangement limits the fuel/air ratio attainable during acceleration of the engine. The output pressure of the air compressor of the engine, which gives the measure of air flow, acts on the upper side of a spring-loaded diaphragm 19 having an abutment with the lever 16 and arranged to increase the fuel flow by closing the vent 12 in response to an increase of compressor pressure, whilst the loading which is a measure of the fuel flow is applied by two opposed springs 22, 25, an abutment 26 for the spring 22 being movable in response to flow of fuel through a variable orifice 29 in the feed conduit 13 to the engine to vary the effective force of the spring 25 which opposes the action of the diaphragm 19. Both the abutment 26 and the throttling member for varying the orifice 29 are movable by a piston 30 which has an inlet 32 to its lower side controlled by a spring-loaded diaphragm 34 subject to the pressure drop across the orifice 29, and an outlet 35 incorporating a restriction 32a. By this arrangement a constant pressure drop is maintained across the orifice 29 and the resultant force of the two springs 22, 25, is a measure of the rate of fuel flow. A capsule 23 balances the effect of pressure acting on the lower face of the diaphragm 19.