A roticulating thermodynamic apparatus (100) having a first fluid flow section (111) and a second fluid flow section (115). The first fluid flow section (111) is configured for the passage of fluid between a first port (114a) and second port (114b) via a first chamber (134a). The second fluid flow section (115) is configured for the passage of fluid between a third port (116a) and a fourth port (116b) via a second chamber (134, 234b). The second port (114b) is in fluid communication with the third port (116a) via a first heat exchanger (302a).

An apparatus comprising: a shaft (18) rotatable about a first rotational axis (30); an axle (20) defining a second rotational axis (32); a first piston member (22) extending from the axle (20) towards a distal end of the shaft (18); a rotor (16) carried on the axle (20); the rotor (16) comprising a first chamber (34a); a housing (12) having a wall defining a cavity (26); a first magnetic guide feature (52); a second magnetic guide feature (50); whereby: the rotor (16) and axle (20) are rotatable with the shaft (18) around the first rotational axis (30); the rotor (16) is pivotable about the axle (20) to permit relative pivoting motion between the rotor (16) and the first piston member (22) as the rotor rotates about the first rotational axis (30); and at least one of the first magnetic guide feature (52) and second magnetic guide feature (50) comprises an electromagnet to pivot the rotor (16) about the axle (20) relative to the first piston member (22).

A compressor and waste heat recovery system is disclosed in which mechanical work from a prime mover along with work generated from the waste heat recovery system are used to operate the compressor. A gas producing system is heated by waste heat from operation of the compressor to produce a stream of gas used to drive a turbine. The turbine is in work communication with the compressor. In one embodiment the gas producing system is a metal hydride. An overrunning clutch can be used with the turbine. In one form multiple gas producing systems are used, one of which to emit gas while the other is used to receive and capture the emitted gas.

A toroidal combustion engine is provided. The toroidal combustion engine includes a first and a second toroidal cylinder which share a single common intersection to define a combustion chamber. The first toroidal cylinder carries a first piston set, while the second toroidal cylinder carries a second piston set. The first and second piston sets are each rotatable about circular paths which are disposed in planes that are perpendicular to one another.

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 transmission assembly for a rotary piston and cylinder device, comprising a rotor including a piston, a stator, a shutter including a slot to receive the piston, and a first gear and a gear sub-assembly, the first gear connectable to a rotatably mounted shutter of the device, and the first gear extending from a side of the shutter, and the first gear connected to the gear sub-assembly which converts rotation to an axis of rotation different to that of the shutter.

A rotary internal combustion engine that has a housing, main rotors with an external cylindrical surface with rigidly fixed gear wheels and blades in the form of gear ledges (protrusions), as well as additional rotors with an external cylindrical surface with rigidly fixed gear wheels and recesses corresponding to the size of the blades on the main rotors. Additionally, the engine includes a unit for preparing and igniting the working mixture and a unit for discharging exhaust gases. Moreover, the circumference values of the main and additional rotors do not match, and are multiples of the length L1 between the nearest points of tangency (physical contact) of the center of the surface of the gear ledge with the housing.

A rotary fluid pressure device, such as a low-speed, high-torque gerotor motor, is provided with a valve drive shaft that is partially inserted into and engaged with a main drive shaft as the main drive shaft engages a rotating output shaft and engages a rotating and orbiting star member of a positive displacement device. The device is also provided with a drive retainer configured to retain the engagement of the main drive shaft and the valve drive shaft.

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 co-rotating scroll is disclosed having a motor having a shaft, a drive scroll connected to the shaft for moving the drive scroll, a driven scroll connected to the drive scroll to be moved by the drive scroll, and an idler shaft for aligning the drive scroll and the driven scroll and for allowing the driven scroll to be moved by the drive scroll.