Gas turbine engine fuel control

Claim 1

A FUEL CONTROL MECHANISM FOR A AS TURBINE ENGINE INCLUDING A COMPRESSOR, SAID FUEL CONTROL MECHANISM COMPRISING A SOURCE OF FUEL UNDER PRESSURE, AN INLET PORT FOR SAID FUEL; AN OUTLET PORT; A CONDUIT COMMUNICATING THEREBETWEEN; FIRST VALVE MEANS IN SAID CONDUIT OPERABLE TO CONTROL FUEL FLOW; AND A CLOSED-LOOP MOMENT BALANCE SYSTEM FOR REGULATING THE FLOW THROUGH SAID CONDUIT, SAID SYSTEM INCLUDING A LEVER AND A BYPASS VALVE MEANS, SAID BYPASS VALVE MEANS INCLUDING A VALVE, A VALVE STEM, A SECOND OUTLET FROM SAID CONDUIT, AND A PASSAGEWAY COMMUNICATING BETWEEN SAID SECOND OUTLET AND SAID SOURCE OF FUEL, SAID STEM BEING PIVOTALLY CONNECTED TO SAID LEVER AT SUBSTANTIALLY RIGHT ANGLES THERETO, A FIRST DEVICE RESPONSIVE TO A SELECTED COMPRESSOR PRESSURE AND FIXEDLY ATTACHED TO SAID VALVE STEM, A SECOND DEVICE RESPONSIVE TO THE DIFFERENCE IN FUEL PRESSURE ACROSS SAID FIRST VALVE MEANS AND PIVOTALLY CONNECTED TO A SECOND POINT ALONG SAID LEVER.