GB810923A - Fuel feed and power control system for gas turbine engines - Google Patents

Abstract

810,923. Gas-turbine plant. BENDIX AVIATION CORPORATION. March 22, 1956 [April 13, 1955], No. 9014/56. Class 110 (2). [Also in Group XXIX] A fuel feed and power control system for a gas-turbine engine comprises a device responsive to a pressure in the compressor for controlling the position of a burner fuel valve, and means responsive to a predetermined value of said pressure for exerting on the fuel valve an action opposing that of the compressor pressure responsive device following generation of the predetermined pressure. The fuel valve 40 is positioned axially by a device 56 set by a pilot's control lever 70 and responsive to compressor inlet temperature and engine speed, and controls fuel flow from pump 34 and pipe 32 to pipe 17 leading to the engine, a regulator valve 46 maintaining a constant pressure drop across the valve. The pump also supplies pressure for rotating valve 40 through piston 62 and rock and pinion 60, 66 via restriction 100 to cylinder 94 at a value determined by a leak-off valve 128 connected to lever 120 and actuated by an evacuated bellows 110 responsive to compressor discharge pressure via 114. The force output of bellows 110, proportional to the compressor pressure, is balanced by the piston loading springs 124, 126. Should the compressor pressure exceed a predetermined value, e.g. during acceleration, it acts via a restriction 140 to open a relief valve 146 so that a bellows 130 collapses a certain amount and rotates a lever 136 which presses on lever 120 and opposes further opening of valve 128.