Patent GB-1198188-A (GB)
Title: Gas Turbine Control System
IPC: F02C7/36
Filed: 1968-12-13
Abstract: 1,198,188. Controlling torque convertors. FORD MOTOR CO. Ltd. 13 Dec., 1968 [2 Jan., 1968], No. 69418/68. Heading F2D. In a vehicle drive comprising a unishaft gas turbine 10 driving a mechanical change-speed transmission 58 through a torque convertor 51, the angle of inclination of the convertor reactor blades 60 is automatically adjusted to vary the loading on the gas turbine shaft 18 to maintain the speed of this shaft constant at the value set by the position of the accelerator pedal, or throttle lever, 112. As shown, the blades are adjusted by a servomotor 70 acting through crank pins 65 on a hub 66, and positioned by fluid pressure 111 from a pump 82 via a control valve 84 positioned by opposed forces from an engine driven governor 102 and the pedal 112 acting through a cam 116 and spring 118. Gas turbine 10 comprises turbine wheels 12, 14 and a compressor 16. The wheels and compressor may be of the radial or axial flow type, and be single or multi-staged. To prevent compressor surge or overheating of the turbines, the fuel delivery from a turbine-driven fuel pump 26 is automatically controlled to maintain a desired turbine temperature for any engine speed. The turbine temperature is measured by an electronic probe 44 and the engine speed by a probe 46. Signals from the probes are fed via an amplifier 42 to a temperature-speed error comparator 41 which, if the temperature is above or below that desired for the particular engine speed, a needle valve 50 is positioned to increase or decrease fuel flow through a by-pass line 38. Engine overspeed, e.g. due to the vehicle coasting so that the convertor pump and turbine rotate together rendering the reactor blades inoperative, is limited by the control valve 84 which, when the compressor speed builds-up excessively above the value set by pedal 14, is moved to the left by governor 102 to pressurize a line 121 to a variable resistor 123 in the temperature probe circuit to give a false high temperature reading to restrict the fuel flow and hence reduce compressor speed. This same control serves to limit the maximum horse-power delivered by the gas turbine with variations in ambient temperatures. At wide-open throttle, the reactorblades will abut a stop, which may be adjustable, or the servomotor piston 72 abuts its cylinder end, so that the compressor tends to speed up, and resistor line 121 is again pressurized and fuel flow reduced. Engine braking is provided by a one-way roller or sprag clutch 61 between the converter pump shell 62 and its turbine shaft 56. Again, Fig. 4 (not shown) an hydraulic control circuit for the gas turbine includes a governor (46<SP>1</SP>) providing a pressure signal (146) dependent on the speed of compressor shaft 18 and delivered to a set temperature pressure generator (124) which produces a pressure signal (168) indicative of the desired turbine temperature for the engine speed signal (146), the signal (168) acting on one end of a valve (42<SP>1</SP>) controlling fuel flow in a by-pass line (38<SP>1</SP>). The opposite end of valve (42<SP>1</SP>) is acted upon by a signal (184) indicative of the actual turbine temperature and controlled by a needle valve (182) positioned by a bimetallic strip (44<SP>1</SP>) measuring the turbine temperature. Engine overspeed, and limitation of maximum horse power, is again controlled by control valve (84<SP>1</SP>) which connects the turbine temperature signal line (184) to the low pressure inlet port of fuel pump (26<SP>1</SP>) to open the valve (42<SP>1</SP>) in fuel bypass line (38<SP>1</SP>).