There is provided an engine assembly for an aircraft, comprising a heat engine in driving engagement with an engine shaft having a first end coupled to a mechanical gearbox and a second end opposite the first end, an electric generator coupled to the second end to provide a generator output voltage, the electric generator separate from the mechanical gearbox, a power electronics module connected to the electric generator and configured to regulate the generator output voltage to provide a regulated output voltage that meets an electrical power demand of at least one aircraft accessory, and a voltage bus connected to the power electronics module and configured to supply the regulated output voltage to the at least one aircraft accessory.

A coal gasification combined power generation facility includes a feed water supply line that supplies feed water condensed by a condenser to an exhaust heat recovery boiler; a supply adjustment valve that adjusts the flow amount of feed water supplied to the exhaust heat recovery boiler; a turbine bypass line that bypasses a steam turbine and supplies steam to the condenser; and a spray water line that supplies the feed water to the turbine bypass line. The coal gasification combined power generation facility has a bypass operation mode, wherein a control device supplies the feed water to the turbine bypass line and performs a first opening degree control to control the opening degree of the supply adjustment valve so that the amount of feed water supplied to the exhaust heat recovery boiler becomes less than that in a normal operation mode.

A coal gasification combined power generation facility includes a feed water supply line that supplies feed water condensed by a condenser to an exhaust heat recovery boiler; a supply adjustment valve that adjusts the flow amount of feed water supplied to the exhaust heat recovery boiler; a turbine bypass line that bypasses a steam turbine and supplies steam to the condenser; and a spray water line that supplies the feed water to the turbine bypass line. The coal gasification combined power generation facility has a bypass operation mode, wherein a control device supplies the feed water to the turbine bypass line and performs a first opening degree control to control the opening degree of the supply adjustment valve so that the amount of feed water supplied to the exhaust heat recovery boiler becomes less than that in a normal operation mode.

An aspect includes a method for motoring control for multiple engines of an aircraft is provided. A controller can determine a motoring time of a first engine starting system to cool a first engine. The controller can compare the motoring time of the first engine starting system with a motoring time of one or more other engine starting systems of one or more other engines of the aircraft. The motoring time of the first engine starting system can be controlled relative to a tolerance of the motoring time of the one or more other engine starting systems by adjusting the motoring time of the first engine starting system relative to the one or more other engine starting systems in a motoring sequence based on comparing the motoring time of the first engine starting system with the motoring time of the one or more other engine starting systems.

A gas turbine engine includes an engine core including: a compressor system including first, lower pressure, compressor, and a second, higher pressure, compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection, wherein the first flange connection is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor; a nacelle surrounding the engine core and defining a bypass duct between the engine core and the nacelle; wherein an axial midpoint of the radially outer edge is defined as the fan OGV tip centrepoint.

A rotary engine system comprises a first-stage working unit and a second-stage working unit configured to complete two passes of work done simultaneously on the same concentric shaft, and the design of two passes of work is based on the work of the pressure on the pistons and the work done by the turbine through the impulsion of the pressure gas and the expansion of the moving mass released by the turbine. The mode of doing work in two cavities is adopted to complete two passes of work in different cavities, namely the work done under pressure and the work done with the mass released by the turbine, thereby realizing twice utilization of total energy. The new structure of the engine system is capable of improving the engine efficiency obviously.

A toroidal lift force engine is provided. Illustratively, the toroidal lift force engine operates in an enclosed environment without heat and/or expelling particles of any kind, utilizing asymmetric pressure distribution on lift turbine blades solely to generate thrust with the normal component of this lift force, while using the tangential component of this lift force to drive accessories, provide control to the fluid velocity, and/or provide motivation of the fluid's flow. The toroidal lift force engine may be utilized to generate thrust, heat and/or electricity for powering vehicles, homes, etc.

A method includes receiving a command to operate a power load of a power system at a command output power while operating the power load at a reference output power; operating a gas turbine engine of the power system in a maximum regulator mode to increase a power generation of the gas turbine engine when the command output power is greater than the reference output power or in a minimum regulator mode to decrease the power generation of the gas turbine engine when the command output power is less than the reference output power; and coordinating an electric machine power draw from the gas turbine engine with a change in power generation of the gas turbine engine to maintain a rotational speed parameter of the gas turbine engine substantially constant while operating the gas turbine engine in the maximum regulator mode or in the minimum regulator mode.

A system for starting a gas turbine engine includes a rotor drive system and a hydraulic motor system operatively connected to the rotor drive system. A gas turbine engine is operatively connected to the hydraulic motor system for starting the gas turbine engine. A method for starting an engine includes initiating single-engine-operation on a multi-engine aircraft. Single-engine operation includes operating a first engine and powering down a second engine. The method includes running a hydraulic motor system. The hydraulic motor system is driven by the rotor drive system and is operatively connected to the second engine. The method includes identifying a need to start the second engine and starting the second engine using the hydraulic motor system.

A system for starting a gas turbine engine includes a rotor drive system and a hydraulic motor system operatively connected to the rotor drive system. A gas turbine engine is operatively connected to the hydraulic motor system for starting the gas turbine engine. A method for starting an engine includes initiating single-engine-operation on a multi-engine aircraft. Single-engine operation includes operating a first engine and powering down a second engine. The method includes running a hydraulic motor system. The hydraulic motor system is driven by the rotor drive system and is operatively connected to the second engine. The method includes identifying a need to start the second engine and starting the second engine using the hydraulic motor system.