A compound engine assembly with an engine core including at least one internal combustion engine, a compressor, and a turbine section where the turbine shaft is configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft is rotationally supported by a plurality of bearings all located on a same side of the compressor rotor(s) and all located on a same side of the turbine rotor(s), for example all located between the compressor rotor(s) and the turbine rotor(s), such that the compressor rotor(s) and the turbine rotor(s) are cantilevered. A method of driving a rotatable load of an aircraft is also discussed.

A transmission assembly for a rotary piston and cylinder device, comprising a first gear (120) and a gear sub-assembly (15, 16, 17, 18, 19), the first gear connectable to a rotatably mounted shutter (12) 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-vane internal combustion engine of the cat and mouse or scissor type with coordinated rotation of two co-axial shafts with position sensors creating chambers of variable volume for intake, compression, power and exhaust strokes. A reversible electric generator motor on at least one of the shafts with an electronic control system for current, an energy storage unit and electrical load. The total work done and angular speed is calculated or empirically determined while an alternating accelerating or decelerating torque is applied for a continuous, uniform rotation cycle.

The disclosure provides rotary machines that include, in one embodiment, a rotatable shaft defining a central axis A, the shaft having a first end and a second end. The shaft can have a first hub disposed thereon with a plurality of cavities. At least one contour is slidably received into an arcuate cavity in an exterior surface of the hub. The contour has a convex outer surface that cooperates with an inwardly facing curved surface of a housing to form a working volume.

A rotary engine includes an intake port, an exhaust port, a rotor having an intake channel and/or an exhaust channel, and a rotor shaft coupled to the rotor. The rotor shaft has an inflow channel in communication with the intake channel and/or an outlet channel in communication with the exhaust channel. The rotary engine includes a housing having a working chamber formed between the housing and the rotor, the working chamber configured to handle, in succession, an intake phase, a compression phase, a combustion phase, an expansion phase, and an exhaust phase. The inflow channel cyclically communicates with the intake port and forms a passage between the intake port and the working chamber through the rotor shaft and the intake channel. The outlet channel cyclically communicates with the exhaust port and forms a passage between the exhaust port and the working chamber through the rotor shaft and the exhaust channel.

A multiple vane kinetic system produces variation in an enclosed volume between pairs of radial vane sets independent of each other and coaxial with a central axis within a annular casing that encapsulates the vane sets. The system operates in a sequence where the vane sets function as rotating links of the mechanism for a particular period, which is preceded and succeeded by another period where either vane sets successively alternate between being a fixed link and a rotating link of the mechanism and during the former period the volumes between vanes remain constant as long as the vane sets have equal angular velocities, otherwise varies at rates proportional to differing angular velocities. The two time periods are controlled by timing devices actuating vane sets to be coupled and decoupled with a power shaft and the variation in length of two time periods makes roto-dynamic variable displacement machine.

A hydraulic transmission apparatus having at least one declutchable hydraulic motor having radial pistons and connected via two motor ducts, and a casing duct connected to the inside of the casing. The apparatus further has clutching means that, in order to perform the clutching of the motor, are suitable for bringing a first one of the motor ducts to a clutching first pressure that is higher than the pressure in the casing while also making it possible to remove fluid via the casing duct. Disposed on the casing duct, the apparatus further has means for limiting the flow of fluid in said casing duct, in a manner such as to cause the pressure inside the casing to increase during the clutching operation. This apparatus enables clutching to take place gently.

The invention relates to a compression and expansion machine comprising a body (12a) with at least one chamber (12) of revolution about an axis of symmetry, and pistons (14a, 14b, 14c, 14d) rotating about the axis of symmetry and dividing the chamber into cells (15a, 15b, 15c, 15d) rotating with the pistons, said machine furthermore comprising a device (22) for coordinating the movement of said pistons and configured so that, during one rotation cycle, each cell (15a, 15b, 15c, 15d) performs at least one first expansion/contraction cycle corresponding to a stage of compressing a first stream of gas passing through this cell and at least one second expansion/contraction cycle corresponding to a stage of expanding a second stream of gas passing through this cell.

A transmission assembly for a rotary piston and cylinder device, comprising a first gear (120) and a gear sub-assembly (15, 16, 17, 18, 19), the first gear connectable to a rotatably mounted shutter (12) 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 compound engine assembly with an engine core including at least one internal combustion engine, a compressor, and a turbine section where the turbine shaft is configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft is rotationally supported by a plurality of bearings all located on a same side of the compressor rotor(s) and all located on a same side of the turbine rotor(s), for example all located between the compressor rotor(s) and the turbine rotor(s), such that the compressor rotor(s) and the turbine rotor(s) are cantilevered. A method of driving a rotatable load of an aircraft is also discussed.