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 engine is provided for providing torque. The engine includes a housing, a stator, a crank shaft, a rotor and a pair of vanes. The housing has an inner wall with an elliptical profile with major and minor axes. The stator has an outer wall and a double ellipsoid profile corresponding to the major and minor axes. The crank shaft is disposed at a junction of the major and minor axes, rotating about a spin axis orthogonal to the profiles. The rotor has an annular circular profile disposed between the inner and outer walls. The rotor turns on the crank shaft. The vanes radially slide within the rotor as the crank shaft rotates and as the vanes turn within the inner and outer walls.

A rotary engine is provided for providing torque. The engine includes a housing, a stator, a crank shaft, a rotor and a pair of vanes. The housing has an inner wall with an elliptical profile with major and minor axes. The stator has an outer wall and a double ellipsoid profile corresponding to the major and minor axes. The crank shaft is disposed at a junction of the major and minor axes, rotating about a spin axis orthogonal to the profiles. The rotor has an annular circular profile disposed between the inner and outer walls. The rotor turns on the crank shaft. The vanes radially slide within the rotor as the crank shaft rotates and as the vanes turn within the inner and outer walls.

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 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 two stroke internal combustion rotary engine (30) with Zindler curve eccentric ring gear (8) and method of working of a two stroke internal combustion rotary engine (30) with Zindler curve eccentric ring gear is disclosed. The engine (30) has an equilateral triangular rotor (7) with Zindler curve shaped eccentric ring gear (8) with teeth. Output shaft (12) is fixed about to the center of the engine (30) with a center spur gear and it also connected to same sized another one or more spur gear (10) on the side of the center spur gear (11). When engine (30) start working, the rotor (7) and eccentric ring gear (8) will rotate eccentrically along with the side spur gears (10) connected to it, by running over the teeth cuts. Engine cover (16, 17) has a hole (20, 21) to allow a coolant to enter the rotor (7) and excel the heat.

A rotary pump is provided for fluid transfer. The pump includes a planar housing, an elongated rotor, a pair of double-concave blades, fore and aft cover plates, and a gear box. The housing has a circular center cavity, and a pair of circular lateral cavities overlapping the center cavity and disposed along a longitudinal axis. The rotor is disposed on a rotor shaft along a rotation axis perpendicular to the longitudinal axis within the center cavity. The blades flank the rotor and are disposed within their corresponding lateral cavity and turn on corresponding blade shafts parallel to the rotor shaft. The fore and aft cover plates flank the housing along the rotation axis to cover the center and lateral cavities. The blades turn opposite from the rotor.

A rotary pump is provided for fluid transfer. The pump includes a planar housing, an elongated rotor, a pair of double-concave blades, fore and aft cover plates, and a gear box. The housing has a circular center cavity, and a pair of circular lateral cavities overlapping the center cavity and disposed along a longitudinal axis. The rotor is disposed on a rotor shaft along a rotation axis perpendicular to the longitudinal axis within the center cavity. The blades flank the rotor and are disposed within their corresponding lateral cavity and turn on corresponding blade shafts parallel to the rotor shaft. The fore and aft cover plates flank the housing along the rotation axis to cover the center and lateral cavities. The blades turn opposite from the rotor.

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.