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.

An internal combustion engine comprises a plurality of engine units (50A-50C), each having a working space (11), in which two rotary pistons (20, 30) are arranged so as mesh with each other and thereby divide the working space (11) into an inflow region (12) and an outflow region (13). Each engine unit comprises a closable inlet opening (62A-62C) to the inflow region (12) and a closable exhaust gas outlet opening (64A-64C). The internal combustion engine further comprises a feed-line pipe (60) to the inlet openings (62A-62C) and an exhaust gas collection pipe (66) connected to the exhaust gas outlet openings (64A-64C), so that the engine units (50A-50C) are connected in parallel with each other. The internal combustion engine further comprises exhaust gas lines (63A, 63B) which connect the engine units (50A, 50B) with each other in series. In dependence upon a desired power output, a control device (70) operates some of the engine units (50B, 50C) either as internal combustion engines, wherein the respective inlet opening (62B-62C) is opened, or as expansion engines, wherein respective inlet opening (62B-62C) remains closed and the respective rotary pistons (20, 30) are instead driven by exhaust gas flowing in via the respective exhaust gas line (63A, 63B).

There is disclosed a cooling system for a liquid cooled internal combustion power plant housed in an engine compartment in a tail cone of an aircraft. The cooling system has: a tail cone inlet defined through a wall of the tail cone and fluidly communicating with an environment; a wall inlet defined through a firewall of the engine compartment; a blower within the engine compartment and having a blower inlet and a blower outlet, the blower inlet fluidly communicating with the environment via the tail cone inlet, via the wall inlet, and via an interior of the engine compartment; a blower outlet defined through a wall of the aircraft and fluidly communicating with the environment; and a cooling flow path extending from the tail cone inlet to the air outlet and across the wall inlet, the cooling flow path in heat exchange relationship with the power plant.

There is disclosed a cooling system for a liquid cooled internal combustion power plant housed in an engine compartment in a tail cone of an aircraft. The cooling system has: a tail cone inlet defined through a wall of the tail cone and fluidly communicating with an environment; a wall inlet defined through a firewall of the engine compartment; a blower within the engine compartment and having a blower inlet and a blower outlet, the blower inlet fluidly communicating with the environment via the tail cone inlet, via the wall inlet, and via an interior of the engine compartment; a blower outlet defined through a wall of the aircraft and fluidly communicating with the environment; and a cooling flow path extending from the tail cone inlet to the air outlet and across the wall inlet, the cooling flow path in heat exchange relationship with the power plant.

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 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.

An engine includes a housing defining an annular bore and a piston assembly disposed within the annular bore. The engine includes at least one valve configured to oscillate between a first position within the annular bore to allow the piston assembly to travel from a first location proximate to the at least one valve to a second location distal to the at least one valve and a second position to define a combustion chamber relative to the piston assembly at the second location. The engine includes an exhaust gas port disposed in fluid communication with the combustion chamber and a fuel distribution assembly configured to mix fuel from a fuel source and air from an air source into a fuel and air mixture at a location external to the combustion chamber and to deliver the fuel and air mixture to the combustion chamber.

An engine includes a housing defining an annular bore and a piston assembly disposed within the annular bore. The engine includes at least one valve configured to oscillate between a first position within the annular bore to allow the piston assembly to travel from a first location proximate to the at least one valve to a second location distal to the at least one valve and a second position to define a combustion chamber relative to the piston assembly at the second location. The engine includes an exhaust gas port disposed in fluid communication with the combustion chamber and a fuel distribution assembly configured to mix fuel from a fuel source and air from an air source into a fuel and air mixture at a location external to the combustion chamber and to deliver the fuel and air mixture to the combustion chamber.

A turboprop engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system, an air duct in fluid communication with an environment of the aircraft, a heat exchanger received within the air duct having coolant passages in fluid communication with the liquid coolant system and air passages air passages in fluid communication with the air duct, and an exhaust duct in fluid communication with an exhaust of the internal combustion engine. The exhaust duct has an outlet positioned within the air duct downstream of the heat exchanger and upstream of an outlet of the air duct, the outlet of the exhaust duct spaced inwardly from a peripheral wall of the air duct. In use, a flow of cooling air surrounds a flow of exhaust gases. A method of discharging air and exhaust gases in an turboprop engine assembly having an internal combustion engine is also discussed.

A turboprop engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system, an air duct in fluid communication with an environment of the aircraft, a heat exchanger received within the air duct having coolant passages in fluid communication with the liquid coolant system and air passages air passages in fluid communication with the air duct, and an exhaust duct in fluid communication with an exhaust of the internal combustion engine. The exhaust duct has an outlet positioned within the air duct downstream of the heat exchanger and upstream of an outlet of the air duct, the outlet of the exhaust duct spaced inwardly from a peripheral wall of the air duct. In use, a flow of cooling air surrounds a flow of exhaust gases. A method of discharging air and exhaust gases in an turboprop engine assembly having an internal combustion engine is also discussed.