Abstract: A propulsion system and method having means for cooling the combustor liner and throat liner of a rocket casing by endothermic pyrolysis of a hydrocarbon fuel in the fuel passageway which is adjacent to and surrounding the combustor liner and the throat liner. Means is provided for high heat flux to the combustor liner and throat liner from combustion within the rocket casing whereby the temperature of the liners exceeds their thermal limits. Catalyst means are utilized for the endothermic pyrolysis. Hydrocarbon fuel is passed through the fuel passageway; heat is provided from the combustion of fuel in the combustion chamber to the fuel passageway by radiation through the combustor liner and the throat liner; and the hydrocarbon fuel is heated at a temperature sufficient to cause the endothermic pyrolysis of the hydrocarbon in the fuel passageway.

Abstract: A propulsion system which utilizes hydrocarbon and hydrogen fuel, having means for cooling of the combustor liner and throat liner of a rocket casing by endothermic pyrolysis of the hydrocarbon in the presence of hydrogen in the fuel passageway. The hydrogen in the fuel accelerates the rate of endothermic pyrolysis in the fuel passageway which is adjacent to and surrounds the combustor liner and the throat liner. Means is also provided for high heat flux to the combustor liner and throat liner from combustion within the rocket casing so that the temperature of the liners exceeds their thermal limits. By the propulsion system and method, hydrocarbon fuel and hydrogen are passed through the fuel passageway which is adjacent to and surrounds the combustor liner and the throat liner in a rocket casing, and heat from the combustion of fuel and hydrogen in the combustion chamber is provided to the fuel passageway by radiation through the combustor liner and the throat liner.