Abstract: A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

Abstract: A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

Abstract: A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

Abstract: A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

Abstract: A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

Abstract: A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowing outwards through the compression passage; a combustion chamber supported within the compression passage near the maximum radius of the rotor having a closed outer end and combustion chamber gases inlets through which gases enter the combustion chamber, each combustion chamber having a fuel inlet, and; one or more expansion passages in fluidic connection with and extending radially inwards from the combustion chamber within a compression passage and fluidically connecting at or near the rotor axis to a combustion gas outlet tube that extends along the rotor axis, combustion gases created by combustion of fuel with inlet gases within the combustion chamber expanding as they flow inwards through the expansion passage.

Abstract: A thermodynamic machine, comprising: a rotor, configured to rotate about a rotor axis, a working fluid circulation path and a coolant fluid path formed within the rotor, the coolant fluid path fluidically isolated from the working fluid circulation path, the working fluid circulation path spanning radially from the rotor axis to close to the periphery of the rotor; a working fluid circulation drive configured to drive the circulation of a working fluid about the working fluid circulation path; at least one working fluid cooler heat exchanger formed as part of the working fluid circulation path and the coolant fluid path, in use coolant fluid passing through the working fluid cooler heat exchanger to transfer heat from the working fluid to the coolant fluid, and; a working fluid heater in the working fluid circulation path configured to heat a working fluid circulating around the working fluid circulation path.

Abstract: A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowing outwards through the compression passage; a combustion chamber supported within the compression passage near the maximum radius of the rotor having a closed outer end and combustion chamber gases inlets through which gases enter the combustion chamber, each combustion chamber having a fuel inlet, and; one or more expansion passages in fluidic connection with and extending radially inwards from the combustion chamber within a compression passage and fluidically connecting at or near the rotor axis to a combustion gas outlet tube that extends along the rotor axis, combustion gases created by combustion of fuel with inlet gases within the combustion chamber expanding as they flow inwards through the expansion passage.

Abstract: A thermodynamic machine, comprising: a rotor, configured to rotate about a rotor axis, a working fluid circulation path and a coolant fluid path formed within the rotor, the coolant fluid path fluidically isolated from the working fluid circulation path, the working fluid circulation path spanning radially from the rotor axis to close to the periphery of the rotor; a working fluid circulation drive configured to drive the circulation of a working fluid about the working fluid circulation path; at least one working fluid cooler heat exchanger formed as part of the working fluid circulation path and the coolant fluid path, in use coolant fluid passing through the working fluid cooler heat exchanger to transfer heat from the working fluid to the coolant fluid, and; a working fluid heater in the working fluid circulation path configured to heat a working fluid circulating around the working fluid circulation path.

Abstract: A reciprocator restraint assembly for a Z-crank axial piston machine is described. The assembly includes two gimbal arms each linked together at gimbal link joint that intersect at a point T. Point T lying in a medial plane M being defined as the plane passing through the point of coincidence of the crank and crankshaft axes to which the line that bisects the crank angle is normal. Each of the gimbal arms is pivotally mounted at an identical distance L from point T. A cylinder gimbal is pivotally mounted from the cylinder cluster and a reciprocator gimbal is pivotally mounted from the reciprocator. The reciprocator gimbal pivot axis is equidistant from point X and T as is the cylinder gimbal pivot axis.

Abstract: A recipricator restraint assembly for a Z-crank axial piston machine is described. The assembly includes two gimbal arms each linked together at gimbal link joint that intersect at a point T. Point T lying in a medial plane M being defined as the plane passing through the point of coincidence of the crank and crankshaft axes to which the line that bisects the crank angle is normal. Each of the gimbal arms is pivotally mounted at an identical distance L from point T. A cylinder gimbal is pivotally mounted from the cylinder cluster and a recipricator gimbal is pivotally mounted from the recipricator. The recipricator gimbal pivot axis is equidistant from point X and T as is the cylinder gimbal pivot axis.