The present invention relates to an ultra-low emission stored exhaust gas-assisted internal combustion powerplant. The powerplant comprises a variable torque drive turbine connected to a piston compressor through a gearbox. The gearbox comprises a planetary or epicyclic gear to selectively direct power from the drive turbine to the compressor and at least one output shaft. The compressed air is mixed with fuel in a staged combustor, the hot exhaust gasses are used to drive the variable torque drive turbine or cooled and stored in a exhaust gasses storage system.

An electronically speed controlled pulsed supersonic turbine engine powering automotive, drone and electric power generation, energised by breathable, clean renewable energy airflow from 2700 psi integral air-tank energising the engine continuously for 3 hours, replacing the toxic fossil gasoline-diesel energised internal combustion engine with carbon emissions that affects climate change. The turbine blades are turning by pulsed impulse of supersonic airflow from sequentially energised eight manifolds of de Laval convergence-divergence-CD with sonic choking nozzle and supersonic divergence airflow impulsing turbine blades turning them within divergence shroud to atmospheric pressure with turbine nose with engine output shaft supported with bearings supported by the air-tank. An electric pulse generator controls engine shaft speed with voltage pulses to solenoid valves commanding spool valves with airflow from the air-tank with output shaft magnetic speed sensing signal sent back to controller in closed loop adjusting to desired set with pulse amplitude and time duration.

A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°.

A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°.

Various systems are provided for a charge-air cooler system. In one example, a system includes a turbocharger system having at least one compressor and one turbine and configured to provide charge air to an engine. The system also includes a charge-air cooler system having at least one charge-air cooler arranged below the at least one compressor, a turbocharger bracket arranged directly below the charge-air cooler system and shaped to mount the charge-air cooler and the turbocharger system to the engine, and a stator adapter physically coupling an alternator to the engine. The stator adapter includes an accessibility window arranged below the charge-air cooler system. The at least one charge-air cooler is closer to the accessibility window than the turbocharger system.

Turbine engine systems equipped with a fuel deoxygenation system and turboelectric power system are provided. In one aspect, a turbine engine system includes a turboelectric power system having an electric generator operatively coupled with a gas turbine engine. A fuel line provides fuel to the gas turbine engine. A fuel deoxygenation system is positioned along the fuel line for reducing an amount of oxygen in the fuel. A main fuel pump is positioned downstream of the fuel deoxygenation system along the fuel line. An electric motor drives the main fuel pump. An electric generator of a turboelectric power system is operatively coupled with the gas turbine engine and generates electrical power. The electrical power is provided to the electric motor and the fuel deoxygenation system. Heat is recovered from the turboelectric power system and the electric motor and is imparted to fuel provided to the gas turbine engine.

Turbine engine systems equipped with a fuel deoxygenation system and turboelectric power system are provided. In one aspect, a turbine engine system includes a turboelectric power system having an electric generator operatively coupled with a gas turbine engine. A fuel line provides fuel to the gas turbine engine. A fuel deoxygenation system is positioned along the fuel line for reducing an amount of oxygen in the fuel. A main fuel pump is positioned downstream of the fuel deoxygenation system along the fuel line. An electric motor drives the main fuel pump. An electric generator of a turboelectric power system is operatively coupled with the gas turbine engine and generates electrical power. The electrical power is provided to the electric motor and the fuel deoxygenation system. Heat is recovered from the turboelectric power system and the electric motor and is imparted to fuel provided to the gas turbine engine.

A method of monitoring a first freewheel interposed between a first drive shaft of a first engine and a rotor. The state of operation of said first freewheel is correct if the first inlet speed of rotation of the first drive shaft lies in a second range of values corresponding to the current stage of operation while the outlet speed of rotation of the rotor lies in a first range of values corresponding to the current stage of operation.

A method of monitoring a first freewheel interposed between a first drive shaft of a first engine and a rotor. The state of operation of said first freewheel is correct if the first inlet speed of rotation of the first drive shaft lies in a second range of values corresponding to the current stage of operation while the outlet speed of rotation of the rotor lies in a first range of values corresponding to the current stage of operation.

A low-cost rocket includes an atmospheric flight part and an exo-atmospheric flight part, and uses the atmospheric air part to ascend into the atmosphere through the use of propellers for the atmospheric portion of the flight. The atmospheric flight part separates from the exo-atmospheric flight part in the vicinity of the exo-atmosphere and the exo-atmospheric rocket is launched thereupon. The atmospheric flight part descends through the atmosphere using autorotation of the propellers and, if necessary, a soft landing can be affected by controlling the pitch of the propellers just prior to landing.