A compound cycle engine having a rotary internal combustion engine, a first turbine, and a second turbine is discussed. The exhaust port of the internal combustion engine is in fluid communication with the flowpath of the first turbine upstream of its rotor. The rotors of the first turbine and of each rotary unit drive a common load. The inlet of the second turbine is in fluid communication with the flowpath of the first turbine downstream of its rotor. The first turbine is configured as a velocity turbine and the first turbine has a pressure ratio smaller than that of the second turbine. A method of compounding a rotary engine is also discussed.

A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft 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 and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

An engine comprises a compression portion and a combustion portion. The compression portion comprises twin-screw rotors, male engaged with female. The combustion portion comprises twin-screw rotors, male engaged with female. The male compression rotor and the male combustion rotor share a same longitudinal axis, and the female compression rotor and the female combustion rotor share a same longitudinal axis. A combustion plate is disposed between the compression portion and the combustion portion, and prevents flow of gas from the compression portion to the combustion portion, except through a small orifice centrally located on the combustion plate. A valve is affixed to the male rotors adjacent to the combustion plate, covering the lobes of the male rotors and extending beyond the lobes of the male rotors. The valve controls the flow of gas from the compression portion to the combustion portion.

A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a first stage turbine, and a turbocharger is discussed. The first stage turbine includes a rotor in driving engagement with the output shaft between two of the rotary units. The exhaust port of each rotary unit is in fluid communication with the flowpath of the first stage turbine upstream of its rotor. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit. The inlet of the second stage turbine of the turbocharger is in fluid communication with the flowpath of the first stage turbine downstream of its rotor. The first stage turbine has a lower reaction ratio than that of the second stage turbine. A method of compounding at least two rotary engines is also discussed.

A compound cycle engine having a rotary internal combustion engine, a first turbine, and a second turbine is discussed. The exhaust port of the internal combustion engine is in fluid communication with the flowpath of the first turbine upstream of its rotor. The rotors of the first turbine and of each rotary unit drive a common load. The inlet of the second turbine is in fluid communication with the flowpath of the first turbine downstream of its rotor. The first turbine is configured as a velocity turbine and the first turbine has a pressure ratio smaller than that of the second turbine. A method of compounding a rotary engine is also discussed.

Disclosed is a gear pump including a pumping chamber in which a first shaft and a second shaft are rotated about their respective axes, each of the first and second shafts supporting at least one hydraulic-pumping element that hydraulically pumps a fluid in the pumping chamber, the at least one hydraulic-pumping element of each of the first and second shafts being positioned in the pumping chamber and each having at least one first radial projection. In the pumping chamber, each of the first and second shafts further supports at least one mechanical drive pinion that rotates each of the first and second shafts, each mechanical drive pinion having second radial projections. The at least one mechanical drive pinion is separate from the at least one hydraulic-pumping element, and the number of the at least one first radial projection and of the second radial projections is different.

An auxiliary power unit having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft drivingly engaged to the engine shaft, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

A rotary engine casing having at least one end wall of an internal cavity for a rotor including a seal-engaging plate sealingly engaging the peripheral wall to partially seal the internal cavity and a member mounted adjacent the seal-engaging plate outside of the internal cavity. The member and seal-engaging plate having abutting mating surfaces which cooperate to define between them at least one fluid cavity communicating with a source of liquid coolant. When the casing includes a plurality of rotor housings, the end wall may be between rotor housings. A method of manufacturing a rotary engine casing is also discussed.

An engine comprises a compression portion and a combustion portion. The compression portion comprises twin-screw rotors, male engaged with female. The combustion portion comprises twin-screw rotors, male engaged with female. The male compression rotor and the male combustion rotor share a same longitudinal axis, and the female compression rotor and the female combustion rotor share a same longitudinal axis. A combustion plate is disposed between the compression portion and the combustion portion, and prevents flow of gas from the compression portion to the combustion portion, except through a small orifice centrally located on the combustion plate. A valve is affixed to the male rotors adjacent to the combustion plate, covering the lobes of the male rotors and extending beyond the lobes of the male rotors. The valve controls the flow of gas from the compression portion to the combustion portion.

A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a first stage turbine, and a turbocharger is discussed. The first stage turbine includes a rotor in driving engagement with the output shaft between two of the rotary units. The exhaust port of each rotary unit is in fluid communication with the flowpath of the first stage turbine upstream of its rotor. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit. The inlet of the second stage turbine of the turbocharger is in fluid communication with the flowpath of the first stage turbine downstream of its rotor. The first stage turbine has a lower reaction ratio than that of the second stage turbine. A method of compounding at least two rotary engines is also discussed.