Abstract: An air intake suitable for an aerospace propulsor comprises a duct which contains, in flow series, a first heat exchanger, a water separator, and a cryogen injector and a second heat exchanger. Air entering the intake is cooled by the first heat exchanger to cause the majority of the water vapor in the air to condense into water droplet form. The water droplets are then removed by the air flow by the water separator. The cryogenic injector reduces the air flow temperatures still further so that any remaining water in the air flow is converted to small dry ice crystals which do not block the second heat exchanger.

Abstract: An air intake suitable for an aerospace propulsor comprises a duct in which are provided two pirmary heat exchangers arranged in parallel relationship and a secondary heat exchanger downstream of the primary heat exchangers. The primary and secondary heat exchangers are arranged to place a cryogenic fluid in heat exchange relationship with the air flow through the duct. Icing of the primary heat exchangers is controlled by interrupting the flow of cryogenic fluid to each of the primary heat exchanger in turn. Thus while one heat exchanger is subject to ice accretion hereon, the temperature of the other increases sufficiently for de-icing thereof to occur.

Abstract: An aerospace propulsor is powered by liquid hydrogen. The hydrogen is passed through a turbine which drives a liquid oxygen pump. During non-atmospheric flight, the liquid oxygen is directed to the propulsor's combustion chamber where it is mixed with the liquid hydrogen and combustion takes place. However during atmospheric flight, the liquid oxygen is pumped to drive a turbine which powers a fan adapted to provide additional pressurization of air entering the engine for combustion.

Abstract: A marine propulsion unit which is mounted externally of a marine vessel and receives supplies of compressed air and fuel from on board the vessel, comprises a housing, a duct in the housing, containing a ventilated flow rotor, the rotor having tip blading driven by the products of combustion from combustion apparatus located in the housing.

Abstract: A dynamic, self sustaining and self perpetuating, device for the production of motive force by combining cryogenic and thermodynamic principles into one system, keeping the systems separated, two open to atmosphere, the other closed, sealed, pressurized and utilizing special compounded fluids, which when alternately exposed to the heat of atmospheric temperature, then, to the coldness of a liquid or an air cooled condensor, first evaporates, then condenses. Rapid expansion during evaporation produces a high pressure vapor which operates an engine and a generator, which are an integral part of the closed system. Rapid condensation drastically reduces back pressure on the aft side of the engine, and the engine operates on the difference between the two pressures, producing electricity, or, the engine can be used as a direct drive for vehicles or equipment. Built in safeguards and alternatives are a part of the systems, assuring continuance of operation despite adverse conditions.