Fuel control system responsive to ambient conditions for combustion turbine power plants

Claim 1

A CONTROL SYSTEM FOR LIMITING THE POWER OUTPUT OF AN AIRCRAFT GAS TURBINE POWER PLANT OF THE TURBOPROP TYPE PROVIDED WITH A COMPRESSOR DRIVEN BY A GAS TURBINE, WITH PROPELLER MEANS DRIVEN BY SAID TURBINE THROUGH REDUCTION GEARING MEANS, AND WITH ADJUSTABLE FUEL SUPPLY MEANS FOR SUPPLYING VARIABLE QUANTITIES OF FUEL TO SAID POWER PLANT, COMPRISING FIRST CONTROL MEANS OPERATIVELY CONNECTED WITH SAID FUEL SUPPLY MEANS FOR SELECTIVELY ADJUSTING THE QUANTITY OF FUEL SUPPLIED TO SAID POWER PLANT, SECOND CONTROL MEANS OPERATIVELY CONNECTED WITH SAID FUEL SUPPLY MEANS FOR LIMITING THE MAXIMUM AMOUNT OF FUEL SUPPLIED TO SAID POWER PLANT IN DEPENDANCE ON OPERATING VARIABLES TO PREVENT OVERHEATING OF SAID TURBINE AND OVERLOADING OF SAID REDUCTION GEARING MEANS, AND THIRD CONTROL MEANS OPERATIVELY CONNECTED WITH SAID FUEL SUPPLY MEANS FOR DECREASING WITHIN A PREDETERMINED ALTITUDE RANGE THE QUANTITY OF FUEL SUPPLIED TO SAID TURBINE IN DEPENDENCE UPON AN OPERATING PRESSURE VARIABLE, SAID THIRD CONTROL MEANS INCLUDING PRESSURE RESPONSE MEANS AND BEING EFFECTIVE TO NORMALLY OVERRIDE AND RENDER INEFFECTIVE SAID SECOND CONTROL MEANS WITHIN SAID PREDETERMINED ALTITUDE RANGE, SAID THIRD CONTROL MEANS BEING EFFECTIVE TO PROVIDE A SUBSTANTIALLY CONSTANT POWER OUTPUT