A method for injecting a reductant into an exhaust gas stream of a combustion turbine engine for selective catalytic reduction. The method may include the steps of: directing the exhaust gas stream through an exhaust duct; receiving the directed exhaust gas for treatment by a catalyst positioned within the exhaust duct; providing a reductant in a liquid state; pressurizing and heating the reductant in a manner that maintains the reductant in the liquid state; and injecting the heated, pressurized reductant into the exhaust gas stream such that the reductant flash vaporizes upon injection due to a pressure differential.

A system and method for supercharging a combined cycle system includes a forced draft fan providing a variable air flow. At least a first portion of the air flow is directed to a compressor and a second portion of the airflow is diverted to a heat recovery steam generator. A control system controls the airflows provided to the compressor and the heat recovery steam generator. The system allows a combined cycle system to be operated at a desired operating state, balancing cycle efficiency and component life, by controlling the flow of air from the forced draft fan to the compressor and the heat recovery steam generator.

An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and 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.

An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and 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.

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.

A hybrid engine includes a gas turbine engine having at least one compressor rotor connected to be driven by at least one turbine rotor. A combustor is connected to receive compressed air from the at least one compressor rotor, and to receive fuel. At least one electric motor is connected to drive the at least one compressor rotor to supplement drive in combination with the at least one turbine rotor. A hybrid engine controller includes processing circuitry and a memory storing instructions that, when executed cause the processing circuitry to control a flow of the fuel to the combustor, control the at least one electric motor. Feedback is received on an operating condition of the hybrid engine indicative of a failure of the at least one electric motor. The at least one compressor is controlled in a first mode to operate at a compressor pressure ratio spaced from a stall pressure ratio that could result in a stall of the at least one compressor based on the operating condition not indicating a potential failure of the at least one electric motor. The at least one compressor is controlled to move to a second mode where the compressor pressure ratio is closer to the stall pressure ratio than in the first mode based on the hybrid engine controller determining that a failure of the at least one electric motor failure occurred. A method is also disclosed.

An electric machine of a gas-turbine engine, the electric machine comprising: a stator; and a rotor configured to rotate around the stator, the rotor comprising: a rotor body having an inner surface and an outer surface; magnets; and one or more retention rings attached to the rotor body and configured to radially retain the magnets to the inner surface of the rotor body.

An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and 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.

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.