A gas-cycle system operable using a Bell-Coleman cycle, the gas-cycle system comprising an expander (23) and a compressor (27) incorporated in a flow path (13). The expander (23) and compressor (27) are integrated in a rotary machine (41), and each comprises a rotor assembly (70) configured to define one or more zones (80) each of which changes continuously in volume during a rotation cycle of the rotor assembly. The expander (23) and compressor (27) are drivingly interconnected whereby rotational drive applied to one is transmitted directly to the other. Each rotor assembly (70) comprises an inner rotor (73) and an outer rotor (75) adapted to rotate about parallel axes at different rotational speeds. The inner rotors (73) are each drivingly connected to a common shaft for rotation therewith. The two outer rotors (75) are coupled together such that rotational drive applied to one is transmitted directly to the other. An air-cycle system and an air conditioning system (10) based on the gas-cycle system are also disclosed.

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.

There is disclosed an aircraft engine assembly including an engine having an engine shaft; an output shaft; a clutch in driving engagement between the engine shaft and the output shaft. The clutch has a first component in driving engagement with the engine shaft and a second component. The clutch is operable between first and second configurations. In the first configuration, the first component is rotatable relative to the second component and the engine shaft is rotatable relative to the output shaft. In the second configuration, the first and second components are engaged with one another and the engine shaft rotates with the output shaft. A mechanical lock is operable between first and second positions. In the first position, the mechanical lock is disengaged from the first component. In the second position, the first and second components are secured for joint rotation one relative to the other.

There is disclosed an aircraft engine assembly including an engine having an engine shaft; an output shaft; a clutch in driving engagement between the engine shaft and the output shaft. The clutch has a first component in driving engagement with the engine shaft and a second component. The clutch is operable between first and second configurations. In the first configuration, the first component is rotatable relative to the second component and the engine shaft is rotatable relative to the output shaft. In the second configuration, the first and second components are engaged with one another and the engine shaft rotates with the output shaft. A mechanical lock is operable between first and second positions. In the first position, the mechanical lock is disengaged from the first component. In the second position, the first and second components are secured for joint rotation one relative to the other.

A new method and approach to have a compact engine having capability of running on both Fuel and Electricity. Engine will be capable of giving high power and better efficiency based on need. Engines can be operated together as well as independently while giving an option to choose the fuel, power and efficiency.

A new method and approach to have a compact engine having capability of running on both Fuel and Electricity. Engine will be capable of giving high power and better efficiency based on need. Engines can be operated together as well as independently while giving an option to choose the fuel, power and efficiency.

A composite piston machine has two moving assemblies of a rotor and a composite piston placed 180° out of phase with each other and linked to a shaft eccentrically placed inside the inner cavity of a main body that has ports for the inlet and outlet of fluids from it. This inner cavity is covered by two lids and divided in two working chambers by a separator. The composite pistons move following the rotation of the rotors while oscillating with respect of them and following the path of skid guides carved in separator and lids, dividing each working chamber in inlet and outlet chambers of variable volume, and intermittently obstructing the inlet and outlet of fluids from the inner cavity through the ports. The machine is designed for compressing gases or pumping liquids and can also operate as an engine driven by compressed gases or with pressurized liquids.

A rotary piston and cylinder device (1) comprising a rotor (2), a stator (4) and a rotatable shutter (3), a rotary piston and cylinder device comprising a rotor, a rotatable shutter, the rotor comprising a piston (5), the piston comprising a first side (5b) and a second side (5a), the first side (5b) arranged to seal with a slot of the shutter, and comprises a working face, the second side being a substantially oppositely directed side to the first side, and the second side (5a) comprising a sealing portion arranged to seal with the shutter slot and/or stator and a non-sealing portion arranged not to seal with the shutter slot.

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 internal combustion engine includes one or more pairs of non-meshing, externally timed rotors disposed within a housing in an expander module and a compressor module. Each rotor includes a cylindrical, center main body including a first end, a second end opposite the first end, an elongate portion extending between the ends and a first peripheral surface portion and a second peripheral surface portion and a bore extending through a center of the main body from the first end to the to second end. The rotors each have a groove extending along outer peripheral edge portions of the rotor. A pair of tip seals is disposed in the grooves. A pair of apex seals is disposed on the first peripheral surface portion and the second peripheral surface portion and an axially floating end plate is disposed at an end of the housing.