A rotary internal combustion engine includes outer and inner housings defining an enclosure therebetween, and first and second side housings disposed on opposite sides of the outer housing. The inner housing is rotatable relative to the outer housing, at least one retractable barrier and at least one fixed barrier. The at least one retractable barrier and the at least one fixed barrier are disposed in the enclosure so as to divide the enclosure into a combustion chamber and an exhaust chamber. The at least one retractable barrier is mounted along a pivot axis and is pivotable between an extended position and a retracted position. An intake port, exhaust port, and ignition source are also provided. An exhaust duct extends from within the enclosure to outside the outer housing in a direction tangent to flow in the enclosure.

A rotary internal combustion engine includes outer and inner housings defining an enclosure therebetween, and first and second side housings disposed on opposite sides of the outer housing. The inner housing is rotatable relative to the outer housing, at least one retractable barrier and at least one fixed barrier. The at least one retractable barrier and the at least one fixed barrier are disposed in the enclosure so as to divide the enclosure into a combustion chamber and an exhaust chamber. The at least one retractable barrier is mounted along a pivot axis and is pivotable between an extended position and a retracted position. An intake port, exhaust port, and ignition source are also provided. An exhaust duct extends from within the enclosure to outside the outer housing in a direction tangent to flow in the enclosure.

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 engine is provided, comprising a stator and a rotor rotatably connected thereto. A stator holder with an annular recessed variable track guide groove is on each end of the stator. A sidewall, close to the rotor, of the stator is provided with an arc-shaped combustible gas groove, a combustible gas inlet, a ring-shape groove, a combustion chamber, a decompression device and an exhaust gas outlet. A compression-resistant element is provided in the ring-shape groove. The rotor is provided with a combustible gas piston chamber having a combustible gas piston, a slider slot having slider, and gas exchange channels. The sliders on the same generating line on the rotor and the combustible gas piston are connected fixedly to the same sliding rod in a sliding rod groove, and the two ends of the sliding rod extend into the annular recessed variable track guide groove of the corresponding stator holder.

A rotary engine is provided, comprising a stator and a rotor rotatably connected thereto. A stator holder with an annular recessed variable track guide groove is on each end of the stator. A sidewall, close to the rotor, of the stator is provided with an arc-shaped combustible gas groove, a combustible gas inlet, a ring-shape groove, a combustion chamber, a decompression device and an exhaust gas outlet. A compression-resistant element is provided in the ring-shape groove. The rotor is provided with a combustible gas piston chamber having a combustible gas piston, a slider slot having slider, and gas exchange channels. The sliders on the same generating line on the rotor and the combustible gas piston are connected fixedly to the same sliding rod in a sliding rod groove, and the two ends of the sliding rod extend into the annular recessed variable track guide groove of the corresponding stator holder.

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.

An internal combustion rotary engine that produces mechanical torque is provided. The engine includes an annular planar housing, a rotor, and first and second valves. The planar housing has a substantially circular annulus flanked by first and second cavities and an axial shaft disposed between the cavities. The rotor is disposed on the shaft and rotates within the annulus; The first and second valves are disposed within respective the cavities. Each valve has an arc wedge having outer convex surface and an inner concave surface, a shaft hole between and parallel to the surfaces along a rocking axis, and a pivot shaft that passes through the shaft hole to enable the wedge to rock back and forth within the cavity.

An internal combustion rotary engine that produces mechanical torque is provided. The engine includes an annular planar housing, a rotor, and first and second valves. The planar housing has a substantially circular annulus flanked by first and second cavities and an axial shaft disposed between the cavities. The rotor is disposed on the shaft and rotates within the annulus; The first and second valves are disposed within respective the cavities. Each valve has an arc wedge having outer convex surface and an inner concave surface, a shaft hole between and parallel to the surfaces along a rocking axis, and a pivot shaft that passes through the shaft hole to enable the wedge to rock back and forth within the cavity.

Disclosed is a rotary engine, comprising a stator and a rotor rotatably connected thereto. A stator holder with an annular recessed variable track guide groove is on each end of the stator. A sidewall, close to the rotor, of the stator is provided with an arc-shaped combustible gas groove, a combustible gas inlet, a ring-shape groove, a combustion chamber, a decompression device and an exhaust gas outlet. A compression-resistant element is provided in the ring-shape groove. The rotor is provided with a combustible gas piston chamber having a combustible gas piston, a slider slot having slider, and gas exchange channels. The sliders on the same generating line on the rotor and the combustible gas piston are connected fixedly to the same sliding rod in a sliding rod groove, and the two ends of the sliding rod extend into the annular recessed variable track guide groove of the corresponding stator holder.