Fuel feeding systems

Claim 1

A FUEL FEEDING SYSTEM OF AN AIRCRAFT ENGINE COMPRISING, A FUEL TANK, FIRST EJECTOR PUMP MEANS HAVING FIRST EDUCTOR MEANS WITH FIRST NOZZLE MEANS THEREIN DISPOSED IN SAID FUEL TANK, A TWO-STAGE PUMP HAVING AN INTAKE LINE, AND AN OUTLET LINE, SAID PUMP BEING LOCATED EXTERNALLY OF SAID FUEL TANK, SAID PUMP INTAKE LINE BEING CONNECTED TO SAID FIRST EDUCTOR MEANS, AND A FIRST PRESSURE BOOST FEEDBACK LINE CONNECTING THE FIRST STAGE OF SAID PUMP TO SAID FIRST NOZZLE MEANS FOR BOOSTING THE PRESSURE IN SAID PUMP INTAKE LINE, SECOND EJECTOR PUMP MEANS HAVING SECOND EDUCTOR MEANS WITH SECOND NOZZLE MEANS THEREIN AND OPERATIVELY DISPOSED IN SAID PUMP INTAKE LINE, AND A SECOND PRESSURE BOOST FEEDBACK LINE HAVING ONE END THEREOF CONNECTED INTO SAID OUTLET LINE OF SAID PUMP AND HAVING THE OTHER END THEREOF CONNECTED TO SAID SECOND NOZZLE MEANS OF SAID SECOND EJECTOR PUMP MEANS IN SAID PUMP INTAKE LINE, AND SAID SECOND STAGE OF SAID PUMP DELIVERING FUEL TO SAID SECOND NOZZLE MEANS AND TO SAID FIRST STAGE OF SAID PUMP AT SUFFICIENT HYDRAULIC PRESSURE TO ENABLE SAID FIRST STAGE TO BE OPERATED IN SUCH A MANNER THAT ANY PRESSURE DIFFERENTIAL ACROSS SAID FIRST STAGE IS RELATIVELY SMALL.