IMPROVEMENTS IN SUPERSONIC AIR INLET CONTROL SYSTEMS FOR A TURBO-PROPULSION ENGINE

摘要

1285086 Gas turbine engine; air intake control GENERAL ELECTRIC CO 16 Dec 1969 [23 Dec 1968] 61210/69 Heading F1G The invention relates to a gas turbine propulsion engine supersonic air intake system having means for varying the air-flow at the engine inlet, also control means for actuating the air-flow varying means so as to maintain the shock wave in the intake in its optimum position, and means proportionately responsive to a rate of change of engine air-flow for causing the control means to actuate the air-flow varying means at a rate proportional to the rate of change in the air-flow. In Fig. 1 a gas turbine ducted fan engine is shown having an air intake 34 the area of which may be controlled by an adjustable centre body through a control 42. A pressure device 44 is provided in the region of the intake throat 36 to sense the position of the intake shock wave and the rate of change of the position thereof. A spill passage 40 controlled by door 39 is provided whereby air in excess of engine requirement may be spilled to atmosphere. Pressure sensors 74, 76 are provided in the fan duct 66 to sense the static pressure PS25 and the total pressure P25 respectively, the pressure signals being passed to duct head sensor 78 and the resulting signal which is a measure of fan duct Mach number M25 passing to differentiator 80 and multiplier 84. A signal responsive to temperature T22 at the inlet to fan 68 is passed to unit 82 and the resulting signal also passed to multiplier 84. The signal M25 from the multiplier is the Mach number derivative and is passed to the summing device 58. The temperature signal is also passed to the unit 92 and then to multiplier 90. A signal indicative of fan speed NF is passed to differentiator 88 and then also to multiplier 90, the signal from the multiplier is the fan speed derivative and is passed to the summing device 58. The shock wave position signal from the sensor 44 is passed to unit 63 together with a signal from the throat area control 42 the resulting signal passing to divider 61 and thence to differentiator 100 and summing device 58. The resulting signal from the summing device is fed to summing device 52 together with a signal from the differentiator 48 which receives a signal from the spill passage 40 closure door 39. The signal from device 52 is fed to the controller 54 which acts to adjust the actuator 56 of the spill passage closure door 39. The throat area control 42 maintains the inlet area as a function of altitude and flight Mach number.