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.

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.

The emergency shutoff device is provided with a casing (21) in which inflow ports (22) through which control oil flows into a space (A1) provided therein and a plurality of outflow ports (23) through which the control oil flows outside of the space (A1) are formed; and a switching unit (24) configured to slide along an inner circumferential surface of the casing (21) in which the space (A1) is formed, to change its position relative to the plurality of outflow ports (23), and thus to switch a circulation state of the control oil in the space (A1). The switching unit (24) switches the circulation state between the first circulation state in which the control oil is circulated from a first inflow port (221) to a first outflow port (231) and the third circulation state in which an open and closed state of a test outflow port (236) is switched while the control oil is being circulated from the first inflow port (221) to the first outflow port (231).

The emergency shutoff device is provided with a casing (21) in which inflow ports (22) through which control oil flows into a space (A1) provided therein and a plurality of outflow ports (23) through which the control oil flows outside of the space (A1) are formed; and a switching unit (24) configured to slide along an inner circumferential surface of the casing (21) in which the space (A1) is formed, to change its position relative to the plurality of outflow ports (23), and thus to switch a circulation state of the control oil in the space (A1). The switching unit (24) switches the circulation state between the first circulation state in which the control oil is circulated from a first inflow port (221) to a first outflow port (231) and the third circulation state in which an open and closed state of a test outflow port (236) is switched while the control oil is being circulated from the first inflow port (221) to the first outflow port (231).

An apparatus for controlling a gas turbine combustor having a diffusion combustion burner and a premix combustion burner comprising: a rotating speed detector for detecting a rotating speed of gas turbine, a recorder for recording the detected value of the rotating speed of gas turbine detected by the rotating speed detector, an arithmetic unit for calculating a change with time of the rotating speed of gas turbine in accordance with details of the detected value of the rotating speed of gas turbine recorded in the recorder, and a fuel control unit for judging a starting situation of reduction in the rotating speed of gas turbine on the basis of the change with time of the rotating speed of gas turbine calculated by the arithmetic unit and controlling respectively a fuel flow rate for the diffusion combustion burner to be fed to the diffusion combustion burner installed in the gas turbine combustor and a fuel flow rate for the premix combustion to be fed to the premix combustion burner.

An apparatus for controlling a gas turbine combustor having a diffusion combustion burner and a premix combustion burner comprising: a rotating speed detector for detecting a rotating speed of gas turbine, a recorder for recording the detected value of the rotating speed of gas turbine detected by the rotating speed detector, an arithmetic unit for calculating a change with time of the rotating speed of gas turbine in accordance with details of the detected value of the rotating speed of gas turbine recorded in the recorder, and a fuel control unit for judging a starting situation of reduction in the rotating speed of gas turbine on the basis of the change with time of the rotating speed of gas turbine calculated by the arithmetic unit and controlling respectively a fuel flow rate for the diffusion combustion burner to be fed to the diffusion combustion burner installed in the gas turbine combustor and a fuel flow rate for the premix combustion to be fed to the premix combustion burner.

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.

A fuel supply system for a turbine engine that provides a modulated thrust control malfunction accommodation (TCMA). The fuel supply system can include a fuel line that fluidly connects a fuel tank and the turbine engine. A fuel pump and a fuel metering valve can be fluidly connected to the fuel line. A bypass line can fluidly connect to the fuel line. Flow through the bypass line can be controlled using a bypass valve and a balancing pressure valve. The TCMA can then modulate the fuel flow using the valves.

A fuel supply system for a turbine engine that provides a modulated thrust control malfunction accommodation (TCMA). The fuel supply system can include a fuel line that fluidly connects a fuel tank and the turbine engine. A fuel pump and a fuel metering valve can be fluidly connected to the fuel line. A bypass line can fluidly connect to the fuel line. Flow through the bypass line can be controlled using a bypass valve and a balancing pressure valve. The TCMA can then modulate the fuel flow using the valves.

A combustion control device including a bleed valve control unit for controlling a bleed valve disposed on a bleed pipe for performing bleeding so that a part of the compressed air flowing into the casing is not used as combustion air in the combustor, a fuel control unit for controlling a fuel regulating valve for regulating a fuel flow rate of fuel supplied to the combustor, and a temperature acquisition unit. Upon reception of a load rejection signal for cutting off a load from the gas turbine, the bleed valve control unit controls a valve opening degree of the bleed valve from a closed state to an open state with a prescribed opening degree, and the fuel control unit controls the fuel regulating valve such that the acquired flame temperature falls within a predetermined temperature range defined by an upper limit value and a lower limit value.