A positive displacement rotary motion device including in one example a pulse detonation device. Also; an indexing system for a rotor assembly where in one example the indexing system regulates the rotational location of drive rotors. In one example the rotors are configured to rotate about a shaft.

A positive displacement rotary motion device including in one example a pulse detonation device. Also; an indexing system for a rotor assembly where in one example the indexing system regulates the rotational location of drive rotors. In one example the rotors are configured to rotate about a shaft.

An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine, a first heat exchanger in fluid communication with the liquid coolant system of the internal combustion engine, a second heat exchanger in fluid communication with the liquid coolant system of the generator, an exhaust duct in fluid communication with air passages of the heat exchangers, and a fan received in the exhaust duct and rotatable by the internal combustion engine for driving a cooling air flow through the air passages. The liquid coolant system of the engine may be distinct from fuel and lubricating systems of the auxiliary power unit. A method of cooling a generator and an internal combustion engine is also discussed.

An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine, a first heat exchanger in fluid communication with the liquid coolant system of the internal combustion engine, a second heat exchanger in fluid communication with the liquid coolant system of the generator, an exhaust duct in fluid communication with air passages of the heat exchangers, and a fan received in the exhaust duct and rotatable by the internal combustion engine for driving a cooling air flow through the air passages. The liquid coolant system of the engine may be distinct from fuel and lubricating systems of the auxiliary power unit. A method of cooling a generator and an internal combustion engine is also discussed.

A turbocharger and method of controlling the same includes a turbine housing comprising an inlet and an outlet, turbine wheel coupled to a shaft. The turbine housing comprising a first scroll and a second scroll for fluidically coupling the inlet and the turbine wheel. The first scroll has a first end adjacent the inlet and a second end adjacent the turbine wheel. The second scroll has a third end adjacent the inlet and a fourth end adjacent the turbine wheel. An exhaust gas diverter valve is coupled to the turbine housing restricting flow into the first scroll or the second scroll.

A turbocharger and method of controlling the same includes a turbine housing comprising an inlet and an outlet, turbine wheel coupled to a shaft. The turbine housing comprising a first scroll and a second scroll for fluidically coupling the inlet and the turbine wheel. The first scroll has a first end adjacent the inlet and a second end adjacent the turbine wheel. The second scroll has a third end adjacent the inlet and a fourth end adjacent the turbine wheel. An exhaust gas diverter valve is coupled to the turbine housing restricting flow into the first scroll or the second scroll.

An aircraft power plant, has: a combustion engine having an outlet outputting combustion gases; a turbine downstream of the combustion engine; a detonation combustion tube fluidly connecting the combustion engine to the turbine; a member having an open position in which the outlet of the combustion engine is fluidly connected to the turbine and a closed position in which the combustion engine is fluidly disconnected from the turbine; a fuel injector fluidly connected to the detonation combustion tube; an igniter operatively connected to the detonation combustion tube; and a controller operatively connected to the fuel injector and to the igniter, the controller configured to, in response to receiving of a command: inject fuel into the detonation combustion tube via the fuel injector, and once the member is in the closed position, power the igniter to ignite a mixture of the combustion gases and the fuel into the detonation combustion tube.

A turbocharger and method of controlling the same includes a turbine housing comprising an inlet and an outlet, turbine wheel coupled to a shaft. The turbine housing comprising a first scroll and a second scroll for fluidically coupling the inlet and the turbine wheel. The first scroll has a first end adjacent the inlet and a second end adjacent the turbine wheel. The second scroll has a third end adjacent the inlet and a fourth end adjacent the turbine wheel. An exhaust gas diverter valve is coupled to the turbine housing restricting flow into the first scroll or the second scroll.

A turbocharger and method of controlling the same includes a turbine housing comprising an inlet and an outlet, turbine wheel coupled to a shaft. The turbine housing comprising a first scroll and a second scroll for fluidically coupling the inlet and the turbine wheel. The first scroll has a first end adjacent the inlet and a second end adjacent the turbine wheel. The second scroll has a third end adjacent the inlet and a fourth end adjacent the turbine wheel. An exhaust gas diverter valve is coupled to the turbine housing restricting flow into the first scroll or the second scroll.

The present invention discloses an internal combustion engine, comprising a compressor, a combustion chamber, a pipeline, a spray pipe, an oil feeder, a driving device, a first safety device, a second safety device, an electric ignition device, a rack, a first bracket arranged on a top of the rack, a second bracket arranged on an upper part of the rack, a third bracket arranged on a lower part of the rack and a fourth bracket arranged on a left part of the rack. The compressor comprises an inner shell and an outer shell, wherein the inner shell comprises an upper pressing plate and a cylindrical plate; the cylindrical plate can move up and down in the cylindrical plate slot; and an outlet is formed in a non-protruding part at the bottom of the outer shell. The internal combustion engine has simple structure and high efficiency.