Electronic fuel control system for gas turbine engines

Claim 1

IN A FUEL CONTROL SYSTEM FOR A GAS TURBINE ENGINE HAVING A COMPRESSOR, THE COMBINATION COMPRISING, A SOURCE OF D.C. VOLTAGE, A SEMICONDUCTOR HAVING A CONTROL TERMINAL AND OUTPUT TERMINALS, A LOAD CIRCUIT INCLUDING A FIRST TEMPERATURE SENSITIVE ELEMENT, A CONTROL ELEMENT, AND SAID OUTPUT TERMINALS CONNECTED ACROSS SAID SOURCE, A BIAS CIRCUIT INCLUDING A SECOND TEMPERATURE SENSITIVE ELEMENT CONNECTING SAID SOURCE AND SAID SEMICONDUCTOR CONTROL TERMINAL TO PROVIDE A BIAS TO SAID SEMICONDUCTOR NORMALLY RENDERING SAID SEMICONDUCTOR CONDUCTIVE, SAID FIRST ELEMENT POSITIONED TO RESPOND TO THE TEMPERATURE OF SAID COMPRESSOR AND PRODUCING AN INCREASE IN CURRENT THROUGH SAID CONTROL ELEMENT IN RESPONSE TO INCREASING TEMPERATURE, AND SAID SECOND ELEMENT POSITIONED TO RESPOND TO THE TEMPERATURE OF SAID COMPRESSOR AND VARYING THE BIAS ON SAID CONTROL TERMINAL TO REDUCE THE CONDUCTION OF SAID SEMICONDUCTOR IN RESPONSE TO FURTHER TEMPERATURE INCREASES TO THEREBY REDUCE THE CURRENT THROUGH SAID CONTROL ELEMENT.