A device serves for the repeated generation of explosions, in particular for the drive of an aircraft. It comprises: .square-solid.a combustion chamber (21), .square-solid.at least one feed line for feeding a flowable, explosive material or components which form an explosive material upon mixing to the combustion chamber (21); .square-solid.a discharge device for the targeted discharge of a gas pressure which is generated by way of ignition of the explosive material in the combustion chamber (21), .square-solid.a movable nozzle regulating element (26) for the partial or complete closure of the discharge device, .square-solid.an actuating element (25) which is configured to open the discharge device further after opening of the discharge device and during an outflow of explosion gases by way of the discharge device. Here, the discharge device has a plurality of part nozzles (40) for the discharge of the gas pressure, and a position of the part nozzles (40) can be set by way of the actuating element (25).

A jet engine (1) with continuous and discontinuous impulse, which comprises a diffuser (2) with a cylindrical exterior shape, a combustion chamber (3), and several fuel injection means (19) and a nozzle (4), both with same exterior shape as the diffuser, a rotating disk chamber (5) that allows air to pass continuously or discontinuously from the diffuser (2) to the combustion chamber (3), an alternative engine with an alternative shaft (13) connected to a main shaft (9) of the engine (1) by means of a first cam (14), several means of stopping the main shaft (9), and a pressurized air chamber (16) connected to the main shaft (9), wherein the fuel injection means (19) are suitable for activating the injection in synchronization with the passage of air from the diffuser (2) to the combustion chamber (3).

A jet engine (1) with continuous and discontinuous impulse, which comprises a diffuser (2) with a cylindrical exterior shape, a combustion chamber (3), and several fuel injection means (19) and a nozzle (4), both with same exterior shape as the diffuser, a rotating disk chamber (5) that allows air to pass continuously or discontinuously from the diffuser (2) to the combustion chamber (3), an alternative engine with an alternative shaft (13) connected to a main shaft (9) of the engine (1) by means of a first cam (14), several means of stopping the main shaft (9), and a pressurized air chamber (16) connected to the main shaft (9), wherein the fuel injection means (19) are suitable for activating the injection in synchronization with the passage of air from the diffuser (2) to the combustion chamber (3).

A constant volume combustion system includes at least one combustion chamber having at least one admission port and an exhaust port. The system also includes at least one elastically deformable tongue made of ceramic matrix composite material forming an air admission valve, the tongue being present inside the chamber and being positioned facing the admission port, the tongue having a first end that is stationary relative to an inside wall of the chamber and a second end, opposite from the first end, the second end being free and movable relative to the inside wall.

A combustion module of a turbine engine, in particular of an aircraft, is configured for carrying out constant-volume combustion. The module includes a plurality of combustion chambers angularly distributed in a regular manner around an axis. Each chamber has an intake port for pressurized gas and an exhaust port for combustion gases. Each intake/exhaust port is configured to be opened or closed by a corresponding common rotating intake/exhaust valve which is coaxial with the axis.

A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

A device and assembly for reliably generating supersonic detonation waves in a fuel and air or fuel and oxygen mixture. The device may use a hemispherical detonation chamber into which reactants, comprising a fuel and air or oxygen mixture are injected and ignited by a laser igniter to initiate a detonation wave. The wave is reflected by the hemispherical geometry of the detonation chamber and may exit the device through a fast-acting valve. The detonation chamber may be then purged and the cycle is repeated many times per second. The device may be used for various applications which include but are not limited to a stand-alone intermittent combustion engine, a pre-detonator for an intermittent combustion engine, a projectile launcher, a cleaning device, acoustical energy generation, pressure energy generation, various manufacturing processes and electric power generation. The device may use liquid, gaseous, or solid fuels, depending on the application.

A device and assembly for reliably generating supersonic detonation waves in a fuel and air or fuel and oxygen mixture. The device may use a hemispherical detonation chamber into which reactants, comprising a fuel and air or oxygen mixture are injected and ignited by a laser igniter to initiate a detonation wave. The wave is reflected by the hemispherical geometry of the detonation chamber and may exit the device through a fast-acting valve. The detonation chamber may be then purged and the cycle is repeated many times per second. The device may be used for various applications which include but are not limited to a stand-alone intermittent combustion engine, a pre-detonator for an intermittent combustion engine, a projectile launcher, a cleaning device, acoustical energy generation, pressure energy generation, various manufacturing processes and electric power generation. The device may use liquid, gaseous, or solid fuels, depending on the application.

An engine, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation/combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the chamber, a fuel supply inlet configured to provide the fuel to the chamber, an air supply channel configured to supply air to the chamber, at least two rotating arms extending radially from the chamber and configured to exhaust gases from detonating the fuel in the chamber and provide a rotational thrust and/or force, and a mechanical work unit configured to receive at least part of the rotational thrust and/or force. Each of the rotating arms has an exhaust nozzle at a distal end thereof, the exhaust nozzle being at or having an angle configured to provide the rotational thrust and/or force.