A power system for an aircraft engine provides rotational drive to propeller driven and turbofan jet engine powered aircraft by use of a propeller or fan drive motor. Electrical power is provided to the drive motor by a high efficiency electrical power generator with reduced electromagnetic drag or reverse torque. The electric generator utilizes a solid state rotor that does not rotate which allows for power generation without reverse torque or the usual energy required to rotate the rotor inside the stator of the generator. Only the magnetic poles of the disclosed rotor rotate to generate the power. The fan blades of the turbofan jet engine are driven by the electric drive motor in which the rotor is a part of the fan as well as the drive from the high pressure turbine.

A power system for an aircraft engine provides rotational drive to propeller driven and turbofan jet engine powered aircraft by use of a propeller or fan drive motor. Electrical power is provided to the drive motor by a high efficiency electrical power generator with reduced electromagnetic drag or reverse torque. The electric generator utilizes a solid state rotor that does not rotate which allows for power generation without reverse torque or the usual energy required to rotate the rotor inside the stator of the generator. Only the magnetic poles of the disclosed rotor rotate to generate the power. The fan blades of the turbofan jet engine are driven by the electric drive motor in which the rotor is a part of the fan as well as the drive from the high pressure turbine.

The present application relates to an electric machine splitting or assembling method, an electric machine assembling method, and an electric machine splitting or assembling device including a sleeving device separating or coaxially sleeving first and second rotary bodies; the first disassembly device fixes the first rotary body and includes at least two first separable portions, and the first rotary body is split into petals in a circumferential direction by disassembling the first separable portions, or its respective petal segments are assembled in the circumferential direction by combining the first separable portions; and the second disassembly device is fixed to the second rotary body and includes at least two second separable portions, and the second rotary body is split into petals in the circumferential direction by disassembling the second separable portions, or its respective petal segments are assembled in the circumferential direction by combining the second separable portions.

A steam generator comprises: a pressure vessel; a gas inlet to the pressure vessel, arranged to receive hydrogen and oxygen under pressure; an ignition means within the pressure vessel, arranged to ignite hydrogen and oxygen received at the gas inlet; a water jacket in or on the pressure vessel; a water inlet arranged to receive water under pressure and feed it to the water jacket; a spray outlet within the pressure vessel; and a steam outlet for the outlet of steam from the pressure vessel. In use, water received at the water inlet passes along the water jacket to provide cooling of the pressure vessel and is output at the spray outlet to provide a water spray (and/or film) that mixes with the ignited hydrogen and oxygen to vaporize the water spray.

An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and an electric machine which has a generally annular shape. The electric machine is mounted coaxially downstream of the fan and has a rotor which is coupled in terms of rotation to the fan, and a stator which is connected to an electronic power circuit by at least one rigid electroconductive bar.

Disclosed is a gas plant (16), in particular for a gas installation (10), comprising an expansion system (18) capable of converting high-pressure gas into low-pressure gas. The gas plant comprises an electricity generating system (30) arranged in parallel with the expansion system (18) and comprising a double-acting actuator (32) comprising two supply ports alternately supplied with high-pressure gas, a hydraulic system (34) connected to the double-acting actuator (32) and configured to transform the mechanical translational energy of the actuator into mechanical rotational energy; and an electricity generator (36) connected to the hydraulic system (34) and configured to convert the mechanical rotational energy into electrical energy.

A hybrid power system for an aircraft comprises a gas turbine connected to a generator for generating electrical power; an electrical storage device configured to output electrical power; a propulsor; a motor operable to drive the propulsor using electrical power from either or both of the generator and the electrical storage device; and a controller. The controller, to meet propulsor power demand, is configured to control an amount of electrical power generated by the generator, and an amount of electrical power outputted by the electrical storage device. In a first control mode coinciding with an increase in the propulsor power demand sufficient to cause a transient excursion of the operating point of a compressor of the gas turbine from a steady state working line, the controller is further configured to temporarily increase the amount of electrical power outputted by the electrical storage device such that the transient excursion is reduced.

A fuel delivery arrangement for a generator can include a throttle-mixing assembly including a mixer body defining a main port extending between an air inlet end and a mixed air-fuel outlet end and defining a fuel inlet port extending into the main port, a Venturi structure located within the main port and being configured to mix fuel received from the fuel inlet port with air received from the air inlet end and to deliver an air-fuel mixture to the air-fuel outlet, a fuel control valve assembly, mounted to the mixer body, including a first valve and a first actuator arranged to control a flow of the fuel passing through the fuel inlet port, and a throttle control valve assembly, mounted to the mixer body, including a second valve and a second actuator arranged to control a flow of the air-fuel mixture passing through the main port.

A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

A method for connecting a power transformer, located between an inverter of a wind turbine and an electrical grid, to the electrical grid; the method comprises the steps gradually increasing a voltage at a primary side of the transformer from a low starting voltage to a target voltage equal or close to a nominal voltage of the transformer, by means of the inverter of the wind turbine or by means of an auxiliary inverter, thereby increasing the voltage at a secondary side of the transformer, wherein the gradually increasing of the voltage uses energy of an internal energy storage device, connecting the secondary side of the transformer to the electrical grid after predefined target conditions have been reached.