Temperature indicating means for gas turbine engines

Claim 1

IN A GAS TURBINE ENGINE COMPRISING, A COMPRESSOR FOR PRESSURIZING AIR, SAID COMPRESSOR HAVING A COMPRESSOR ROTOR, A COMBUSTOR TO WHICH THE PRESSURIZED AIR IS DELIVERED TO SUPPORT COMBUSTION THEREIN, MEANS FOR DELIVERING FUEL TO SAID COMBUSTOR FOR COMBUSTION WITH SAID AIR TO GENERATE A HOT GAS STREAM, A TURBINE COMPRISING A ROTOR AND AN INLET FOR DIRECTING THE HOT GAS STREAM TO DRIVE SAID ROTOR, THE ROTORS OF SAID COMPRESSOR AND TURBINE BEING CONNECTED TO FROM AN ENGINE ROTOR, MEANS FOR INDICATING THE TEMPERATURE AT THE INLET OF SAID TURBINE, SAID INDICATING MEANS COMPRISING, MEANS FOR PRODUCING SIGNAL RESPECTIVELY PROPORTIONAL TO ENGINE ROTOR SPEED, COMBUSTOR INLET AIR TEMPERATURE, COMBUSTOR INLET STATIC PRESSURE, AND RATE OF FUEL FLOW TO THE COMBUSTOR, MEANS RECEIVING THE OUTPUT FROM SAID SIGNAL PRODUCING MEANS FOR GENERATING AN INTERMEDIATE SIGNAL AS A FUNCTION OF THE FUEL FLOW DIVIDED BY THE TURBINE INLET AREA AND THE COMBUSTOR INLET STATIC PRESSURE AND AS A PREDETERMINED FUNCTION OF ENGINE ROTOR SPEED AND OF THE COMBUSTOR INLET STATIC PRESSURE, MEANS FOR ADDING THE OUTPUT SIGNAL FROM SAID TEMPERATURE SIGNAL MEANS TO THE OUTPUT OF SAID INTERMEDIATE SIGNAL GENERATING MEANS, MEANS FOR DERIVING FROM THE OUTPUT SIGNAL OF SAID ADDING MEANS A SIGNAL REPRESENTATIVE OF THE SQUARE ROOT THEREOF AND MULTIPLYING THE OUTPUT FROM SAID INTERMEDIATE SIGNAL GENERATING MEANS BY SAID SQUARE ROOT SIGNAL, WHEREBY SAID INDICATING MEANS PRODUCES AN OUTPUT SIGNAL FROM THE ADDING MEANS ACCURATELY REPRESENTING THE TEMPERATURE AT THE INLET TO SAID TURBINE.