Fuel control system

Claim 2

IN A FUEL CONTROL DEVICE FOR CONTROLLING THE FLOW OF FUEL TO THE COMBUSTION CHAMBER OF AN AIRCRAFT TURBOJET ENGINE HAVING A PRIMARY TURBINE FOR DRIVING AN AIR COMPRESSOR AND A LOWER TURBINE FOR PROPELLING SAID AIRCRAFT; A FUEL SUPPLY PUMP DRIVING BY THE PRIMARY TURBINE, A CONDUIT CONNECTING SAID PUMP TO SAID CHAMBER, A FIRST VALVE IN SAID CONDUIT FOR REGULATING THE FUEL FLOW TO SAID CHAMBER, A FIRT SPEED GOVERNOR, INDEPENDENT OF SAID PUMP, DRIVEN BY SAID PRIMARY TURBINE, AND ACTING ON SAID VALVE, FOR CONTROLLING THE SPEED OF SAID PRIMARY TURBINE; A SECOND SPEED GOVERNOR DRIVEN BY SAID POWER TURBINE, AND MEANS RESPONSIVE TO SAID SECOND GOVERNOR FOR LIMITING THE ACTION OF SAID FIRST POWER TURBINE IS LIMITED BY THE SPEED OF SPEED OF SAID POWER TURBINE IS LIMITED BY THE SPEED OF SAID PRIMARY TURBINE.

Claim 3

AN AIRCRAFT TURBOJET ENGINE FUEL CONTROL APPARTUS COMPRISING; A CONDUIT SUPPLYING FUEL TO SAID ENGINE, A METERING RESTRICTION IN SAID CONDUIT, FIRST LINEARLY MOVALBE MEANS FOR VARYING THE FLOW AREA THROUGH SAID RESTRICTION SECOND MANUALLY-OPERABLE MEANS, AND THIRD ENGINE SPEEDRESPONSIVE MEANS, FOR VARYING THE LINEAR POSITION OF SAID FIRST MEANS; FOURTH CAM MEANS REVERSIBLY POSITIONABLE IN TWO DIFFERENT DIRECTIONS AND HAVING A WARPED SURFACE, FOR LIMITING THE POSITIONING BY SAID SECOND MEANS OF SAID FIRST MEANS; FIFTH MEANS, RESPONSIVE TO ENGINE INDUCTION AIR TEMPERATURE, FOR VARYING THE ADJUSTMENT OF SAID FOUTH MEANS IN ONE DIRECTION, IN ACCORDANCE WITH SAID TEMPERATURE; AND SIXTH MEANS FOR VARYING THE ADJUSTMENT OF SAID FOURTH MEANS, IN THE OTHER DIRECTION, IN ACCORDANCE WITH ENGINE SPEED, WHEREBY THE FUEL FLOW TO SAID ENGINE IS CONJOINTLY CONTROLLED IN ACCORDANCE WITH THE POSITION OF SAID SECOND MEANS, ENGINE SPEED, AND SAID TEMPERATURE; SAID THIRD MEANS INCLUDING A CENTRIFUGAL GOVERNOR, AND SAID FOURTH MEANS BEING OPERATIVELY ASSOCIATED WITH A SEVENTH CONTOURED CAM MEANS FOR VARYING THE GAIN (DWF/D%N) OF SAID GOVERNOR, AS A PRESELECTED FUNCTION OF STEADY-STATE ENGINE SPEED, THEREBY PRODUCING OPTIMUM STABILITY AND RESPONSE CHARACTERISTICS OF SAID GOVERNOR, OVER THE ENTIRE SPEED RANGE OF SAID ENGINE.

Claim 4

AN AIRCRAFT TURBOJET ENGINE FUEL CONTROL APPARTUS COMPRISING; A CONDUIT SUPPLYING FUEL TO SAID ENGINE, A METERING RESTRICTION IN SAID CONDUIT, FIRST LINEARLY MOVALBE MEANS FOR VARYING THE FLOW AREA THROUGH SAID RESTRICTION SECOND MANUALLY-OPERABLE MEANS, AND THIRD ENGINE SPEEDRESPONSIVE MEANS, FOR VARYING THE LINEAR POSITION OF SAID FIRST MEANS; FOURTH CAM MEANS REVERSIBLY POSITIONABLE IN TWO DIFFERENT DIRECTIONS AND HAVING A WARPED SURFACE, FOR LIMITING THE POSITIONING BY SAID SECOND MEANS OF SAID FIRST MEANS; FIFTH MEANS, RESPONSIVE TO ENGINE INDUCTION AIR TEMPERATURE, FOR VARYING THE ADJUSTMENT OF SAID FOUTH MEANS IN ONE DIRECTION, IN ACCORDANCE WITH SAID TEMPERATURE; AND SIXTH MEANS FOR VARYING THE ADJUSTMENT OF SAID FOURTH MEANS, IN THE OTHER DIRECTION, IN ACCORDANCE WITH ENGINE SPEED, WHEREBY THE FUEL FLOW TO SAID ENGINE IS CONJOINTLY CONTROLLED IN ACCORDANCE WITH THE POSITION OF SAID SECOND MEANS, ENGINE SPEED, AND SAID TEMPERATURE; SAID THIRD MEANS INCLUDING A CENTRIFUGAL GOVERNOR, AND SAID FOURTH MEANS BEING OPERATIVELY ASSOCIATED WITH A SEVENTH CONTOURED CAM MEANS FOR VARYING THE GAIN (DWF/D%N) OF SAID GOVERNOR, AS A PRESELECTED FUNCTION OF STEADY-STATE ENGINE SPEED, THEREBY PRODUCING OPTIMUM STABILITY AND RESPONSE CHARACTERISTICS OF SAID GOVERNOR, OVER THE ENTIRE SPEED RANGE OF SAID ENGINE.