Patent ID: 6536208
Filing Date: 2003-03-25
Classification: F02K

Abstract:
A device for supplying fuel for a rocket propulsion unit having a first fuel circuit with a first fuel and at least a second fuel circuit with a second fuel, each fuel being brought to an increased energy level by a pump and being supplied for combustion over an injection head with injection elements, the first fuel being heated in cooling channels extending in a propulsion chamber wall before the fuel is supplied for combustion, and the first fuel subsequently being fed to at least turbines assigned to the pumps,wherein a heat exchanger is provided in which fuel coming from the turbines is in a heat exchange with fuel coming from a pump, wherein the heat exchanger is one of arranged on the injection head and integrated as a unit with the injection head, wherein the heat exchanger comprises a first, a second and a third inlet pipe as well as a first and at least a second outlet pipe, the first inlet pipe leading into a first heat exchanger space which in a heat-conducting manner is connected with a second heat exchanger space, fuel arriving from the first heat exchanger space by way of the first outlet pipe arriving at the cooling channels and fuel arriving by way of the second inlet pipe in the second heat exchanger space being connected with the injection head at least by way of the second outlet pipe, and wherein the first heat exchanger space is connected with at least one heat exchange finger which projects at least partially into a combustion chamber and whose discharge is connected with the first outlet pipe.