Cooling method and means for rocket engines

Claim 1

IN A ROCKET ENGINE, THE COMBINATION OF A THRUST CHAMBER HAVING A COOLANT JACKET FOR THE PASSAGE OF A GIVEN AMOUNT OF LIQUID COOLANT UNDER A GIVEN PRESSURE, A PROPELLANT INJECTOR FOR THE THRUST CHAMBER, LIQUID COOLANT INLET AND OUTLET LINES COMMUNICATING WITH THE COOLING JACKET, A STORAGE TANK FOR A GASEOUS COOLANT, MEANS TO FORCE SAID GIVEN AMOUNT OF LIQUID COOLANT IN A GIVEN TIME THROUGH THE COOLANT INLET LINE AND THE COOLING JACKET OF THE THRUST CHAMBER AND THE COOLANT OUTLET LINE, MEANS TO INJECT GASEOUS COOLANT FROM THE STORAGE TANK INTO THE LIQUID COOLANT INLET LINE FOR MIXTURE WITH THE LIQUID COOLANT TO INCREASE ITS VOLUME AND RESULTANT RATE OF FLOW OF CIRCULATION THROUGH THE COOLING JACKET, A CENTRIFUGAL SEPARATOR CONNECTED TO THE COOLANT OUTLET LINE OF THE COOLING JACKET OF THE THRUST CHAMBER, AND AN INJECTION LINE TO CONDUCT SEPARATED LIQUID COOLANT FROM THE SAID SEPARATOR TO THE PROPELLANT INJECTOR OF THE THRUST CHAMBER.