The present invention relates to a structural arrangement for a stationary internal combustion engine for machines or vehicles (universal), which can use various types of fuel. More specifically, the present invention relates to an internal combustion engine with improved combustion efficiency, improved thermodynamic efficiency, reduced dimensions, an improved power-to-weight ratio that exceeds that of aircraft turbine engines using the Brayton thermodynamic cycle, and up to three times less fuel consumption and gas emissions into the environment.

The present invention relates to a structural arrangement for a stationary internal combustion engine for machines or vehicles (universal), which can use various types of fuel. More specifically, the present invention relates to an internal combustion engine with improved combustion efficiency, improved thermodynamic efficiency, reduced dimensions, an improved power-to-weight ratio that exceeds that of aircraft turbine engines using the Brayton thermodynamic cycle, and up to three times less fuel consumption and gas emissions into the environment.

Rotary vane internal combustion engine comprises of two rotors, nested in each other, placed in a cylindrical housing, wherein each rotor has at least two radial vanes rigidly attached to the rotor that form chambers for intake, compression, combustion, and exhaust. Each rotor, alternately engages with a shaft by overrunning one-way clutches and held from turning back, through the cushioning mechanisms, mounted on flywheels, which are rigidly attached on the shaft, wherein the assembled rotors from the outside are rigidly closed by flanges on each of which is mounted at least one blade, which are placed into formed cavity between rotors and caps of the housing thereby forming two cooling chambers through which coolant circulates around rotors through openings in the housing and through longitudinal grooves in the shaft. On the vanes mounted cylindrical and conical seals that exclude the need for lubrication.

Rotary vane internal combustion engine comprises of two rotors, nested in each other, placed in a cylindrical housing, wherein each rotor has at least two radial vanes rigidly attached to the rotor that form chambers for intake, compression, combustion, and exhaust. Each rotor, alternately engages with a shaft by overrunning one-way clutches and held from turning back, through the cushioning mechanisms, mounted on flywheels, which are rigidly attached on the shaft, wherein the assembled rotors from the outside are rigidly closed by flanges on each of which is mounted at least one blade, which are placed into formed cavity between rotors and caps of the housing thereby forming two cooling chambers through which coolant circulates around rotors through openings in the housing and through longitudinal grooves in the shaft. On the vanes mounted cylindrical and conical seals that exclude the need for lubrication.

A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.

A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.

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 method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.

A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.