Fuel control mechanism for a gas turbine engine

Claim 1

A FUEL CONTROL SYSTEM FOR A GAS TURBINE ENGINE HAVING A COMPRESSOR AND A COMBUSTOR WITH A FUEL NOZZLE, COMPRISING: (A) MEANS FORMING A BODY WITH A VALVE PORTION AND AN ACTUATOR PORTION, SAID VALVE PORTION HAVING A BORE WITH SPACED FUEL INLET AND OUTLET PORTS, THE INLET PORT BEING ADAPTED FOR CONNECTION WITH A PRESSURIZED FUEL SOURCE AND THE OUTLET BEING ADAPTED FOR CONNECTION WITH THE FUEL NOZZLE OF THE GAS TURBINE; (B) VALVE MEANS IN SAID BORE FOR CONTROLLING COMMUNICATION BETWEEN SAID INLET AND OUTLET PORTS; (C) MERANS NORMALLY TENDING TO MOVE SAID VALVE TOWARD A CLOSED POSITION; (D) VALVE ACTUATING MEANS IN SAID ACTUATOR PORTION INCLUDING A PLUNGER AND MOVABLE WALL ASSEMBLY, SAID ASSEMBLY HAVING FIRST AND SECOND OPPOSED WALL SURFACES ADAPTED TO BE EXPOSED TO DIFFERENTIAL COMPRESFACES ADAPTED TO BE EXPOSED TO DIFFERENTIAL COMPRESPILED TO THE FIRST WALL SURFACE AND TENDIONG TO CAUSE SAID ACTUATING MEANS TO OPEN SAID VALVE; (E) MEANS RESPONSIVE TO THE SPEED OF THE GAS TURBINE ENGINE TO CONTROLLABLY VENT AND THUS LIMIT THE PRESSURE APPLIED TO SAID FIRST WALL SURFACE; AND (F) MEANS RESPONSIVE TO A PREDETERMINED INCREASE IN TURBINE OPERATING TEMPERATURE TO INCREASE THE PRESSURE APPLIED TO SAID SECOND WALL SURFACE IRRESPECTIVE OF THE CONDITION OF OPERATION OF SAID SPEED RESPONSIVE MEANS TO CAUSE SAID ACTUATING MEANS TO CLOSE SAID VALVE.