Multiple-propellant air vehicle and propulsion system

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. The hydrocarbon fuel is heated in the presence of the hydrogen at a temperature sufficient to cause the endothermic pyrolysis of the hydrocarbon in the fuel passageway, and the heat removed from the combustion through the combustor liner and throat liner reduces the temperature in the combustion chamber at the combustor liner and the throat liner so the thermal limits of the combustor liner and throat liner are not exceeded while the hydrogen in the fuel accelerates the rate of pyrolysis of the hydrocarbon.

Dependencies are inferred from the claim text.