Abstract: A power management system for a multi engine rotorcraft having a main rotor system with a main rotor speed. The power management system includes a first engine that provides a first power input to the main rotor system. A second engine selectively provides a second power input to the main rotor system. The second engine has at least a zero power input state and a positive power input state. A power anticipation system is configured to provide the first engine with a power adjustment signal in anticipation of a power input state change of the second engine during flight. The power adjustment signal causes the first engine to adjust the first power input to maintain the main rotor speed within a predetermined rotor speed threshold range during the power input state change of the second engine.

Abstract: In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.

Abstract: A gas turbine engine system includes an engine component comprising ceramic matrix composite materials, at least one control system configured to control at least a temperature of the engine component, and a controller. The controller includes a degradation map stored therein. The degradation map includes degradation fields, each field defined by a unique range of temperatures and stresses of the component and correlated to different types of degradation of the component. The controller is configured to determine a first temperature and stress of the component and a first field based on the first temperature and stress, determine a second field different from the first and a second temperature and stress that would locate the component in the second field, and instruct the control system to change the temperature of the component from the first to the second temperature to locate the component in the second field.

Abstract: The present disclosure relates to a method for controlling the propulsion of a ship (10). The ship (10) comprises an engine (5) and a controllable pitch propeller (7), wherein torque and engine speed are adjusted to correspond to an output set point value. The adjustment is such that the ship (10) is operated in an operating condition with an engine speed of the engine (5) and a propeller pitch of the controllable pitch propeller (7) such that the fuel consumption of the ship (10) is brought and/or held within a desired fuel consumption range. The method comprises determining a top pressure value indicative of a top pressure in at least one cylinder (9) and reducing the torque of the engine (5) upon detection that the lop pressure value exceeds a top pressure threshold value.

Abstract: The present disclosure is directed to a system for controlling an output of a gas generator via an operator manipulated input device. The system includes one or more sensors measuring one or more environmental conditions, a gas generator shaft speed, and a power turbine torque. The system further includes an operator manipulated input device and one or more controllers including one or more processors and one or more memory devices. The one or more memory devices stores instructions that when executed by the one or more processors cause the one or more processors to perform operations.

Abstract: A control apparatus for controlling a compressor driven by a driving unit generating driving power by a gas turbine and an electric motor includes: a temperature detection section for detecting an exhaust gas temperature of the gas turbine; and a control section for generating a motor torque instruction value for the electric motor based on the detected exhaust gas temperature. Such a control apparatus can realize a control so as not to distribute a load on the electric motor when the exhaust gas temperature of the gas turbine is low and a driving power is low. As a result, the operation efficiency can be enhanced.

Abstract: A fuel metering system for supplying fuel to load includes a variable displacement piston pump having an adjustable hanger that is movable to a plurality of positions. The variable displacement piston pump is configured to receive a drive torque and, upon receipt of the drive torque, to supply fuel to the plurality of loads at a flow rate dependent on the position of the adjustable hanger. A hanger actuator is coupled to receive hanger position commands and is operable, in response thereto, to move the adjustable hanger to the commanded position.

Abstract: The present application and the resultant patent provide a gas turbine engine. The gas turbine engine may include a compressor for compressing a flow of air, a combustor for combusting the flow of air and a flow of fuel to create a flow of combustion gases, a turbine driven by the flow of combustion gases, a rotor driven by the turbine and driving the compressor, a rotor speed sensor, and a gas turbine shut down controller. The gas turbine shut down controller varies the flow of fuel to the combustor based upon a rotational speed of the rotor as determined by a dynamic target trajectory schedule.

Abstract: A system for generating accessory power from a gas turbine engine is provided by the present invention. The system includes an electronic control device for monitoring at least one parameter which provides information about an incipient change in power demand, a control valve operated by the control device for supplying bleed air from the engine during a transient state in response to the at least one monitored parameter, and a pneumatically operated device for receiving the bleed air and for generating power to operate equipment onboard an aircraft. The pneumatically operated device may be an air turbine or a pneumatically integrated generator.

Abstract: A fuel metering system for supplying fuel to load includes a variable displacement piston pump having an adjustable hanger that is movable to a plurality of positions. The variable displacement piston pump is configured to receive a drive torque and, upon receipt of the drive torque, to supply fuel to the plurality of loads at a flow rate dependent on the position of the adjustable hanger. A hanger actuator is coupled to receive hanger position commands and is operable, in response thereto, to move the adjustable hanger to the commanded position.

Abstract: An engine speed detector detects an engine speed of an engine having a baseline torque versus engine speed curve. A torque sensor detects an engine torque of the engine. A data processor determines if the detected engine speed is within a first speed range and if the detected engine torque is within a first torque range. A motor controller activates an electric motor to rotate substantially synchronously with a corresponding engine speed associated with the detected engine torque in an electric propulsion mode in accordance with a supplemental torque versus engine speed curve if the detected engine speed is within the first speed range and if the detected engine torque is within the first torque range. The supplemental torque versus engine speed curve intercepts the baseline torque versus engine speed curve at a lower speed point and a higher speed point.

Abstract: A method for operating a gas turbine engine is provided. The method comprises coupling at least one sensor within the gas turbine engine to transmit a signal indicative of a rotational speed of a rotor assembly within the gas turbine engine, detecting oscillations of the rotor assembly based on the signal transmitted from the at least one sensor, comparing detected oscillations to a predetermined oscillation threshold, and generate an output to facilitate fuel flow adjustments during non-engine operational periods, wherein the fuel flow adjustments facilitate reducing oscillations of the rotor assembly during engine operation.

Abstract: Applicant's Differential-Pressure Torque Measurement System generates the torque signal from a differential gas pressure measured across the power turbine. The gas pressure differential is measured by using two pressure taps, the first tap taking the pressure reading of the expanding gas as the gas travels from the gas-generating turbine to the power turbine of the engine and the second tap taking the pressure reading of the gas as it escapes the engine through the exhaust port. The differential between the two pressure readings is determined. The pressure differential is then input to a processor which processes it in a pre-determined fashion along with the rotational speed signal of the power turbine, initial pressure and the temperature measurements of the air as the air is initially inlet into the engine. The result of the processing are various engine parameter indications including the torque.