An electric module for an aircraft turbomachine includes an electric machine stator having an annular shape around an axis (A) and being configured to surround a rotor of the electric machine, and an annular support element of the stator. The support element includes an outer annular surface configured to be swept over by a gas stream (F) from the turbomachine with a view to conductively cooling the stator.

Supersonic jet engine includes a housing and an exhaust nozzle. Spike extends outwardly from the housing. Plurality of fans are arranged in an axial direction within the housing, each of the plurality of fans includes a plurality of fan blades. Plurality of turbines are included, and each of the plurality of turbines having a plurality of turbine blades and being arranged and coupled to a respective one of the fans in a radial direction. Plurality of radial compressors are located radially from the each of the plurality of turbines and are operable to drivingly rotate the respective turbine, which in turn rotates the respective fan. Plurality of electric motors are included, and each of the plurality of electric motors are coupled to a respective one of the plurality of radial compressors and drivingly rotating the respective radial compressor.

An integral propulsion and auxiliary power generation system includes a rocket engine, a liquid propellant supply system, an auxiliary electrical system, and a transmission system. The liquid propellant supply system is configured to supply a liquid fuel and a liquid oxidizer to the rocket engine. The liquid propellant supply system includes a gas generator configured to burn a mixture of the liquid fuel and the liquid oxidizer to generate a combustion gas stream, and a gas turbine configured to convert the kinetic energy of the combustion gas stream into mechanical energy. The auxiliary electrical system includes a power generator configured to convert mechanical energy into electrical energy and an electric load device electrically coupled to the power generator. The transmission system is configured to mechanically couple the gas turbine and the power generator to selectively transfer mechanical energy between the gas turbine and the power generator.

An engine system is provided that includes an engine rotating structure, an electric machine rotating structure and a flex coupler. The flex coupler rotatably connects the electric machine rotating structure to the engine rotating structure. The flex coupler includes a first mount, a second mount and a flex plate. The first mount includes a plurality of first mount fingers arranged circumferentially about an axis. The second mount includes a plurality of second mount fingers arranged circumferentially about the axis. The flex plate connects the first mount to the second mount. The flex plate includes a plurality of first flex plate fingers and a plurality of second flex plate fingers. Each of the first flex plate fingers is attached to a respective one of the first mount fingers. Each of the second flex plate fingers is attached to a respective one of the second mount fingers.

Modifications to power plants for moderating climate warming and increasing safety combine a large compressed air energy storage (CAES) system with a thermal power plant such that free power plant waste heat replaces natural gas used at existing and planned CAES facilities. The system allows higher percentages of wind and solar energy on existing grids. The compressed air in a companion CAES can cool a nuclear reactor during an emergency. Also an inexpensive, add-on, external, Emergency Core Cooling System (ECCS) can cool a nuclear reactor after shutdown, even when all internal cooling water circulation has been disabled. All embodiments are installed outside the plant where they will not be damaged in the event of a plant accident. Both systems use environmentally friendly compressed air energy storage in new ways, and can be built and installed quickly around the world at existing plants using only proven infrastructure.

Modifications to power plants for moderating climate warming and increasing safety combine a large compressed air energy storage (CAES) system with a thermal power plant such that free power plant waste heat replaces natural gas used at existing and planned CAES facilities. The system allows higher percentages of wind and solar energy on existing grids. The compressed air in a companion CAES can cool a nuclear reactor during an emergency. Also an inexpensive, add-on, external, Emergency Core Cooling System (ECCS) can cool a nuclear reactor after shutdown, even when all internal cooling water circulation has been disabled. All embodiments are installed outside the plant where they will not be damaged in the event of a plant accident. Both systems use environmentally friendly compressed air energy storage in new ways, and can be built and installed quickly around the world at existing plants using only proven infrastructure.

A system includes a nitrous oxide (NOx) conversion system configured to treat emissions from a conversion system, and includes a selective catalytic reduction (SCR) catalyst assembly and a temperature sensor disposed upstream of the SCR catalyst assembly to measure temperature of an exhaust before flowing into the SCR catalyst assembly. The NOx conversion system includes a temperature sensor downstream of the SCR catalyst assembly to measure a temperature of a treated exhaust flow after exiting the SCR catalyst assembly and a controller coupled to the SCR catalyst assembly. The controller receives signals representative of the temperatures to generate a first control signal representative of a desired temperature to heat the exhaust to. The controller receives the first control signal to output a second control signal to regulate a temperature of the exhaust upstream of the SCR catalyst assembly via a heating system.

An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

A dual cycle system for generating shaft power using a supercritical fluid and a fossil fuel. The first cycle is an open, air breathing Brayton cycle. The second cycle is a closed, supercritical fluid Brayton cycle. After compression of air in the first cycle, the compressed air flows through a first cross cycle heat exchanger through which the supercritical fluid from the second cycle flows after it has been compressed and then expanded in a turbine. In the first cross cycle heat exchanger, the compressed air is heated and the expanded supercritical fluid is cooled. Prior to expansion in a turbine, the compressed supercritical fluid flows through a second cross cycle heat exchanger through which also flows combustion gas, produced by burning a fossil fuel in the compressed air in the first cycle. In the second cross cycle heat exchanger, the combustion gas is cooled and the compressed supercritical fluid is heated.

The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterised in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).