Fuel feed systems for gas turbines such as turbojet engines

Claim 1

A POWER PLANT FOR AN HELICOPTER COMPRISING, IN COMBINATION, A ROTOR HAVING VARIABLE PITCH BLADES, A GAS TURBINE, MEANS FOR CONNECTING SAID TURBINE TO SAID ROTOR IN ORDER TO DRIVE THE LATTER, A GENERAL-PITCH CONTROL PLATE CONNECTED TO SAID BLADES IN ORDER TO MODIFY THE GENERAL PITCH OF SAID BLADES INDEPENDENTLY OF THE ACTUATION TIME OF SAID PLATE, A FUEL FEED PUMP DELIVERING FUEL AT A DETERMINABLE PRESSURE, A FUEL FEED LINE INTERCONNECTING SAID PUMP AND SAID GAS TURBINE AND HAVING AN ADJUSTABLE FLOW PASSAGE, CONVENTIONAL MEANS CONNECTED TO SAID TURBINE FOR ADJUSTING SAID FLOW PASSAGE IN RELATION TO THE GAS TURBINE SPEED INDEPENDENTLY OF SAID CONTROL MEMBER TO MAINTAIN A CONSTANT TURBINE SPEED, A PRESSURE REDUCER HAVING A SLIDEVALVE SLIDABLY MOVABLE ACROSS THE FUEL LINE UPSTREAM OF SAID ADJUSTABLE FLOW PASSAGE IN ORDER TO ADJUST THE SECTIONAL AREA OF FUEL FLOW BETWEEN THE FUEL PUMP AND SAID ADJUSTABLE FLOW PASSAGE, A MEMBRANE AND A RESILIENT DEVICE MAINTAINING SAID SLIDE-VALVE IN BEARING ENGAGEMENT WITH SAID MEMBRANE; A PLUNGER, A SPRING INTERPOSED BETWEEN SAID MEMBRANE AND SAID PLUNGER, THE PLUNGER HAVING A NOZZLE IN THE BOTTOM THEREOF, A HYDRAULIC CHAMBER INSIDE WHICH SAID PLUNGER MOVES, A LINE CONNECTING SAID HYDRAULIC CHAMBER TO THE FUEL LINE DOWNSTREAM OF SAID ADJUSTABLE FLOW PASSAGE, A CAM BEARING ON SAID PLUNGER AND AN INTERCONNECTING MEMBER BETWEEN SAID CAM AND SAID GENERAL-PITCH CONTROL PLATE.