An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, wherein the plurality of circuits of cooling channels are interwoven together; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling each of the plurality of circuits of cooling channels to at least one supply of cooling fluid, wherein, in each of the plurality of circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.

An engine fuel control system includes a fuel metering valve operable to control the flow of fuel between a supply line and a delivery line. The delivery line is configured to receive fuel from one or more fuel pumps. The engine fuel control system further includes a pressure raising arrangement which receives the fuel flow from the delivery line and raises the fuel pressure therein. The engine fuel control system further includes a pressure sensor arranged to sense the pressure of the fuel in the supply line between the one or more fuel pumps and the fuel metering valve, or to sense the pressure of the fuel in the delivery line between the fuel metering valve and the pressure raising arrangement.

In an embodiment, a rotorcraft includes: a plurality of engines; a flight control computer connected to the plurality of engines, the flight control computer being configured to: receive an operating parameter of a first engine of the plurality of engines; determine an engine output ramping rate for the first engine according to a difference between the operating parameter of the first engine and a nominal limit of the first engine; and increase the output of the first engine in response to detecting an outage of another engine of the plurality of engines, the output of the first engine being increased according to the engine output ramping rate.

Vane assemblies for turbine engines are described. The vane assemblies include a vane having an internal cavity and a vane platform and a vane rail defining, in part, an outer diameter supply cavity. A blade outer air seal support (BOAS support) is arranged adjacent the vane and engages with a portion of the vane, the blade outer air seal support having BOAS support rail, and a BOAS supported on the BOAS support and engaging with a portion of the vane. The BOAS support includes a first cooling flow aperture configured to enable a cooling flow to cool at least the BOAS and a second cooling flow aperture formed in the BOAS support rail. The vane rail includes a third cooling flow aperture to form a cooling flow path through the second cooling flow aperture and the third cooling flow aperture to fluidly connect to the outer diameter supply cavity.

A turbomachine for a vehicle is provided. The turbomachine includes a manifold configured to channel a flow of fluid therethrough; a first pressure measurement device in communication with the manifold and configured to determine a first pressure difference; a second pressure measurement device in communication with the manifold and configured to determine a second pressure difference; a data selector device in communication with the first pressure measurement device and the second pressure measurement device, wherein the data selector device receives the first and second pressure difference and uses a logic circuit to generate a single pressure signal; and an engine controller operably coupled to the data selector device such that the engine controller receives the single pressure signal indicating a pressure differential of the manifold.

A method for operating a power plant, having at least one gas turbine engine and at least one fuel gas compressor, includes supplying fuel gas through a utility supply line, compressing the fuel gas to a plant supply pressure in the operating fuel gas compressor, and supplying the compressed fuel gas to a plant supply line. The gas turbine engine is operated at a set power output according to a power demand signal. If a failure of an operating fuel gas compressor is detected, the power output of the gas turbine engine is reduced to an emergency power output (which is lower than the set power output), and the power output of the gas turbine engine is restricted to the emergency power output. The reduction of the power output is performed in one single step and is controlled by at least one feedforward control signal.

A gas turbine engine comprises a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine to, in turn, drive the gear architecture. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil system operates to ensure that the gear reduction will be adequately supplied with lubricant for at least 30 seconds at power should the main oil supply system fail.

An engine control system includes an electronic hardware engine controller in signal communication with an actuator and an engine sensor. The actuator operates at a plurality of different positions to control operation of an engine. The engine sensor measures an engine operating parameter. The engine controller generates a synthesized engine operating parameter, and adjusts the position of the actuator based on the synthesized engine operating parameter in response to detecting a faulty engine sensor.

A coolant delivery system for a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, each independent circuit of cooling channels including a plurality of headers and a plurality of feed tubes fluidly coupling the plurality of headers to a supply of cooling fluid; and an impingement plate connected to the exterior wall of the component by the plurality of feed tubes of the independent circuits of cooling channels, wherein, in each of the plurality of independent circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes and the plurality of headers into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.

In accordance with one embodiment, a fan controller operates in a standard mode when main power is provided to the power supply unit in which speed of the fan is controlled in response to a primary pulse width modulation (PWM) signal from a power controller. A loss of the main power to the power supply unit may be detected at a logic circuit, which provides a secondary PWM signal to the fan controller in response to the loss of the main power. In certain embodiments, the fan controller is operated in a power loss mode in response to the secondary PWM signal to direct the speed of the fan to a low-power consumption target speed.