A self-rotation graphene heat-dissipation device for a direct-drive electro-hydrostatic actuator, that includes inner and outer walls of a shell eccentrically arranged relative to each other, the shell sleeves on an outer side of a self-rotation mechanism. The self-rotation mechanism is arranged on an outer side of a shaft; the shaft is coaxial with the inner wall of the shell and connected with outer and inner end covers. The self-rotation mechanism includes a rotor and blades, the rotor sleeves on the shaft and is connected with the outer and inner end covers. The rotor is slidably connected with the blades, and outer walls of the blades are closely attached to the inner wall of the shell. Graphene heat-dissipation layers are coated on outer walls of all of the shell, blades, the rotor, the inner and outer end covers respectively.

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

A rotary internal combustion engine has: a rotor; a housing circumscribing a rotor cavity, the rotor received within the rotor cavity, the housing having a peripheral wall and a side housing assembly secured to the peripheral wall, the side housing assembly having plates located at spaced apart ends of the peripheral wall, the plates defining seal running surfaces in sealing engagement with opposed end faces of the rotor, the plates made of silicon carbide.

A rotary internal combustion engine has: a rotor; a housing circumscribing a rotor cavity, the rotor received within the rotor cavity, the housing having a peripheral wall and a side housing assembly secured to the peripheral wall, the side housing assembly having plates located at spaced apart ends of the peripheral wall, the plates defining seal running surfaces in sealing engagement with opposed end faces of the rotor, the plates made of silicon carbide.

A rotary engine, parts thereof, and methods associated therewith is provided. The engine is modular and adjustable to accommodate a variety of requirements and preferences. The system includes a combustion assembly having a housing and a power rotor positioned therein. The power rotor rotates in a first direction from the beginning of each combustion process through the end of each exhaust process. The system also includes a compression assembly linked to the combustion assembly such that the compression rotor rotates in the first direction from the beginning of each intake process through the end of each compression process. A tank assembly in fluid communication with the compression assembly and the combustion assembly provides stability to the system while eliminating or otherwise reducing transitional loses.

A scroll device includes a fixed scroll with a first involute and a first cooling chamber; an orbiting scroll with a second involute and a second cooling chamber, the orbiting scroll mounted to the fixed scroll via a mechanical coupling, the orbiting scroll configured to orbit relative to the fixed scroll around an orbital axis; a flexible conduit in fluid communication with the first cooling chamber and the second cooling chamber, the flexible conduit extending around the orbital axis from a first side of the scroll device to a second side of the scroll device; and an integrated aftercooler.

An internal combustion engine includes a housing defining an internal cavity, an inner body sealingly moving within the internal cavity for defining at least one combustion chamber of variable volume, a pilot subchamber in communication with the at least one working chamber, an ignition element in communication with the pilot subchamber, a main injector communicating with the at least one combustion chamber, and a pilot injector having a tip in communication with the pilot subchamber. The tip of the pilot injector includes at least a first injection hole defining a first spray direction and a second injection hole defining a second spray direction different from the first spray direction. The first spray direction extends toward the communication between the pilot subchamber and the at least one working chamber. A method of performing combustion in an internal combustion engine is also discussed.

A method of operating a thermal exchange engine having a thermal energy conduction surface and rotating elements in the vessel which form a plurality of closed working chambers which increase or decrease in volume as the rotating elements move. The method involves placing a phase change fluid in each of the working chambers and operating the vessel as on a closed cycle without addition of phase change fluid into the vessel or removal of phase change fluid from the vessel. The method involves applying thermal energy to the thermal energy conduction surface, thereby thermally increasing or decreasing a pressure inside at least one working chamber positioned adjacent to the thermal energy conduction surface, such that the change in pressure inside the at least one working chamber causes the rotating elements to move the at least one working chamber away from the thermal energy conduction surface.

A method of operating a thermal exchange engine having a thermal energy conduction surface and rotating elements in the vessel which form a plurality of closed working chambers which increase or decrease in volume as the rotating elements move. The method involves placing a phase change fluid in each of the working chambers and operating the vessel as on a closed cycle without addition of phase change fluid into the vessel or removal of phase change fluid from the vessel. The method involves applying thermal energy to the thermal energy conduction surface, thereby thermally increasing or decreasing a pressure inside at least one working chamber positioned adjacent to the thermal energy conduction surface, such that the change in pressure inside the at least one working chamber causes the rotating elements to move the at least one working chamber away from the thermal energy conduction surface.