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.

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.

A method of igniting liquid fuel in a turbomachine combustor is provided. The method includes a step of initiating a flow of gaseous fuel from a gaseous fuel supply to a gaseous fuel nozzle. The method further includes a step of initiating a flow of liquid fuel from a liquid fuel supply to a primary liquid fuel cartridge. After initiating both the flow of gaseous fuel and the flow of liquid fuel, the method includes a step of igniting the flow of gaseous fuel and the flow of liquid fuel with an igniter. The method further includes a step of terminating the flow of gaseous fuel from the gaseous fuel supply to the gaseous fuel nozzle.

A method and system of controlling a turboprop engine are described. The method comprises obtaining a propeller speed and a pressure-based measurement signal from a torque pressure transducer coupled to the turboprop engine, determining an output power of the turboprop engine from the pressure-based measurement and the propeller speed, calculating a gas generator speed request based on an error between the output power and a reference power, determining a fuel flow command based on the gas generator speed request, and issuing the fuel.

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.

Systems, apparatus, and methods to a flame out valve for a gaseous fuel system are disclosed. An example apparatus to reduce fuel combustion comprises: a first valve connected to a fuel supply line, the first valve including: a first plug to control a flow of fuel; a first spring coupled to a first end of the first plug; and a first magnet coupled to a second end of the first plug; a second valve connected to a purge system in parallel with the fuel supply line, the second valve including: a second plug to control a flow of a gas; a second spring coupled to a first end of the second plug; and a second magnet coupled to a second end of the second plug, the second magnet magnetically coupled to the first magnet; and an electromagnetic actuator coupled to at least one of the first or the second valve.

A combustion staging system has: a splitter; pilot and mains fuel manifolds; mains flow control valves; and fuel servo line. Each mains flow control valve has a chamber containing a piston, the chamber to a piston mains side fed by the mains fuel manifold, and the chamber to a piston servo side fed by the servo line. The piston has an open pilot-and-mains position allowing flow from the chamber mains side to the respective injector mains discharge orifice. The piston prevents flow from the chamber mains side. The piston is movable under a pressure change in the servo line relative to the mains fuel manifold. The system has a servo pump and a hydraulic motor driving it. The servo pump changes fuel pressure. Motive power for the hydraulic motor is fuel diverted from a fuel pump high pressure output, the motor returning the diverted fuel to a low pressure input.

A fuel metering system includes a metering valve having a first inlet fluidly coupled to a source of fluid at a first pressure, a second inlet, a first outlet and a second outlet. The metering valve includes a slot, and a valve body movable to control an amount of fluid supplied to the first and second outlet. The fuel metering system includes a servo valve fluidly coupled to the second inlet and to a second source of fluid at a second pressure. The servo valve is in fluid communication with the second inlet and a body of the servo valve is movable to supply a fluid to move the valve body. The slot is configured to variably restrict the flow of the fluid through the second outlet to balance a force applied by a biasing member. The fuel metering system includes a fixed flow restriction downstream of the second outlet.

An aircraft fuel system can include a fuel line configured to transport fuel therein, an exposed aircraft structure in direct or indirect thermal communication with the fuel in the fuel line to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure. The exposed aircraft structure can include at least one internal fuel channel in fluid communication with the fuel line for direct thermal communication with the fuel. The system can include a fuel/fluid heat exchanger in fluid communication with the fuel line to transfer heat from the fuel to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.