Methods and systems for method for managing a hybrid-electric powerplant (HEP) comprising a thermal engine and an electric motor are described. The method comprises transmitting a thermal power command to the thermal engine to generate a thermal power output; transmitting an electric power command to the electric motor to generate an electric power output; comparing the thermal power output to the thermal power command and the electric power output to the electric power command; detecting a fault when the thermal power output deviates from the thermal power command or when the electric power output deviates from the electric power command; and accommodating the fault by modulating the thermal power command in response to a deviation in the electric power output and modulating the electric power command in response to a deviation in the thermal power output.

Control systems and methods suitable for combination with power production systems and methods are provided herein. The control systems and methods may be used with, for example, closed power cycles as well as semi-closed power cycles. The combined control systems and methods and power production systems and methods can provide dynamic control of the power production systems and methods that can be carried out automatically based upon inputs received by controllers and outputs from the controllers to one or more components of the power production systems.

An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.

An aircraft propulsion system comprises first and second thrust producing gas turbine engines. The system comprises a controller configured to determine a required overall propulsion system thrust level, and determine an engine core power level contribution from each aircraft gas turbine engine such that the overall propulsion system produces a minimum overall noise level and meets the required overall propulsion system thrust level. In meeting the minimum overall noise level, at least the first and second gas turbine engines are operated at different engine core power settings.

A method and a system for synthesizing output power provided by an engine are provided. The engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the engine, a pressure of fluid at an exit of the compressor section, a temperature upstream of the exit of the compressor section, and a fuel flow rate to the engine are determined. A synthesized value of output power provided by the engine is determined based on a product of at least a first factor, a second factor, and a third factor, the first factor being a function of the pressure, the second factor being a function of the temperature, and the third factor being a function of the fuel flow rate. The synthesized value of output power provided by the engine is output.

A large frame heavy duty industrial gas turbine engine that can produce twice the power as a conventional single spool industrial engine, and can operate at full power during a hot day. The industrial engine includes a high spool that directly drives an electric generator at a synchronous speed of the electric power grid, a low spool with a low pressure turbine that drives a low pressure compressor from the exhaust gas from the high pressure turbine, where the low pressure compressor supplies compressed air to the high pressure compressor. Variable inlet guide vane assemblies are used in the low pressure turbine and the low pressure compressor so that the high spool can operate at full power even during a hot day. The low spool is designed to operate at a higher speed than at the normal temperature conditions so that a high mass flow can be produced for the high spool during the hot day conditions.

A method and apparatus for the operation of a gas turbine unit with an evaporative intake air cooling system in the intake air pathway, wherein the return water flow of the evaporative intake air cooling system is used for the cooling of components of the gas turbine unit and/or of a generator coupled to the gas turbine unit and/or of another element coupled to the gas turbine unit, and a gas turbine unit adapted to be operated using this method.

The method effects control upon engines, in particular to regulating power of a gas-turbine-generator system used in gas-turbine locomotives, hybrid locomotives, etc. A control signal for the fuel metering unit actuator is formed by an electronic engine control system on the basis of processing of a signal from a turbine rpm sensor and a design value of the generator active electric output power. The system power can be preset. A preset power value is compared to a real power calculated value which is obtained according to measured values of current and voltage. An obtained difference is taken as the basis for forming a control signal for the fuel metering unit actuator in order to provide a certain turbine rpm and a control signal for a current regulator supplying energy to the generator excitation winding in accordance with the load curve of the gas turbine-generator system.

The present disclosure relates to systems and methods that are useful in control of one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants, methods of starting power production plants, and methods of generating power with a power production plant wherein one or more control paths are utilized for automated control of at least one action. The present disclosure more particularly relates to power production plants, control systems for power production plants, and methods for startup of a power production plant.

A turbine control unit and method for controlling a turbine, in particular for controlling the start-up of a turbine, the unit being designed as a cascade controller having a master controller and an inner controller, the master controller being a thermal stress controller for the components subjected to thermal stress.