An internal combustion engine, includes a 1st rotor having two blades, rotating in the circular volume of the motor body block with variable angular speed; a 2nd rotor having two blades, rotating in the circular volume of the motor body block with variable angular speed, a rolling bearing provided between the 1st rotor and the 2nd rotor enables rotation of the 1st rotor and the 2nd rotor on each other; a 1st unidirectional rolling bearing between the 1st rotor and the back cover enables rotation of the 1st rotor and the 2nd rotor at different times and at different extents; a 3rd unidirectional rolling bearing transferring the 2nd rotor's rotation movements to the output shaft is provided on the internal collar of the 2nd rotor; a 4th unidirectional rolling bearing transferring the 1st rotor's rotation movements to the output shaft is provided on the internal collar of the 1st rotor.

An internal combustion engine, includes a 1st rotor having two blades, rotating in the circular volume of the motor body block with variable angular speed; a 2nd rotor having two blades, rotating in the circular volume of the motor body block with variable angular speed, a rolling bearing provided between the 1st rotor and the 2nd rotor enables rotation of the 1st rotor and the 2nd rotor on each other; a 1st unidirectional rolling bearing between the 1st rotor and the back cover enables rotation of the 1st rotor and the 2nd rotor at different times and at different extents; a 3rd unidirectional rolling bearing transferring the 2nd rotor's rotation movements to the output shaft is provided on the internal collar of the 2nd rotor; a 4th unidirectional rolling bearing transferring the 1st rotor's rotation movements to the output shaft is provided on the internal collar of the 1st rotor.

An assembly for an aircraft having a propeller, including a wheel well for a retracted landing gear, first and second cooling ducts; and an engine assembly having an engine shaft configured for driving engagement with the propeller, the engine assembly including a coolant circulation system for circulation of a liquid coolant, a lubricant circulation system for circulation of a lubricant, a first heat exchanger in fluid communication with at least the coolant circulation system, and a second heat exchanger in fluid communication with at least the lubricant circulation system. Each heat exchanger is positioned and configured for receiving a cooling airflow from the respective cooling duct. The wheel well is located between the heat exchangers. A method of cooling a lubricant and a liquid coolant of an engine assembly is also discussed.

An assembly for an aircraft having a propeller, including a wheel well for a retracted landing gear, first and second cooling ducts; and an engine assembly having an engine shaft configured for driving engagement with the propeller, the engine assembly including a coolant circulation system for circulation of a liquid coolant, a lubricant circulation system for circulation of a lubricant, a first heat exchanger in fluid communication with at least the coolant circulation system, and a second heat exchanger in fluid communication with at least the lubricant circulation system. Each heat exchanger is positioned and configured for receiving a cooling airflow from the respective cooling duct. The wheel well is located between the heat exchangers. A method of cooling a lubricant and a liquid coolant of an engine assembly is also discussed.

A rotary internal combustion engine includes outer and inner housings defining an enclosure therebetween, and first and second side housings disposed on opposite sides of the outer housing. The inner housing is rotatable relative to the outer housing, at least one retractable barrier and at least one fixed barrier. The at least one retractable barrier and the at least one fixed barrier are disposed in the enclosure so as to divide the enclosure into a combustion chamber and an exhaust chamber. The at least one retractable barrier is mounted along a pivot axis and is pivotable between an extended position and a retracted position. An intake port, exhaust port, and ignition source are also provided. An exhaust duct extends from within the enclosure to outside the outer housing in a direction tangent to flow in the enclosure.

A rotary internal combustion engine includes outer and inner housings defining an enclosure therebetween, and first and second side housings disposed on opposite sides of the outer housing. The inner housing is rotatable relative to the outer housing, at least one retractable barrier and at least one fixed barrier. The at least one retractable barrier and the at least one fixed barrier are disposed in the enclosure so as to divide the enclosure into a combustion chamber and an exhaust chamber. The at least one retractable barrier is mounted along a pivot axis and is pivotable between an extended position and a retracted position. An intake port, exhaust port, and ignition source are also provided. An exhaust duct extends from within the enclosure to outside the outer housing in a direction tangent to flow in the enclosure.

The fluid transfer apparatus includes a rotor housing for forming a fluid compression space having the shape of an epitrochoid surface; a rotor eccentrically rotates inside the fluid compression space by being eccentrically coupled to a rotation shaft; and a rotor housing cover covering the fluid compression space of the rotor housing and including a rotation shaft penetration hole formed at the center of the cover, and a first cover fluid channel and second cover fluid channel are symmetrically formed on the opposite sides of each other with the rotation shaft penetration hole in the middle, wherein a plurality of rotor housing covers are arranged to be spaced apart from each other, one rotor housing is arranged between every two rotor housing covers, one rotor is arranged in the fluid compression space of each rotor housing, and each rotor is arranged to face a different direction from a neighboring rotor.

Systems and methods for detecting at least one non-functional combustion chamber of an engine comprising a plurality of combustion chambers are described herein. In response to detecting a partial output power loss of the engine, one of the plurality of combustion chambers is assessed by monitoring an engine parameter indicative of an output power of the engine, determining whether a change in the engine parameter has occurred, when the change has occurred, determining that the combustion chamber is functional, and when no change has occurred, determining that the combustion chamber is non-functional and discontinuing fuel injection to the non-functional combustion chamber.

A method of operating a rotary engine including a rotor engaged to a shaft and rotationally received in a housing to define a plurality of working chambers of variable volume, including delivering a pilot quantity of fuel into a pilot cavity in successive communication with the working chambers, igniting the pilot quantity of fuel within the pilot cavity, and delivering a main quantity of fuel into the working chambers downstream of the successive communication of the pilot cavity with the working chambers, where at least one of the pilot quantity and the main quantity is varied between successive rotations of the shaft.

A rotor assembly for a rotary internal combustion engine is provided. The rotor assembly includes a rotor having a radial groove defined radially in a peripheral surface of the rotor. The groove has a depth and an intermediate shoulder at an intermediate depth. The groove has a first width therealong that is narrower than an intermediate width at the shoulder. An apex seal is received in the groove and protrudes from the peripheral face of the rotor. The apex seal is configured to move radially between a first position and a second position outward of the first position. A biasing member biases the apex seal toward the second position. A platform is disposed in the groove between the apex seal and the biasing member and has a width greater than the first width.