A control device is a device for controlling a gas turbine. The control device is provided with: a prediction unit configured to predict a future state quantity of the gas turbine corresponding to a control input to the gas turbine in a prediction horizon, using a prediction model; an optimization unit configured to optimize the control input in at least a part of the prediction horizon, using a prediction result of the prediction unit; a storage unit for storing sensitivity information indicating sensitivity of the control input to a change speed of the state quantity for each operating condition of the gas turbine; and an update unit configured to read the sensitivity information corresponding to the operating condition assumed in the prediction horizon from the storage unit, and update one or more coefficients of a prediction equation of the state quantity used in the prediction model.

A fuel system including a fuel tank, a first pump fluidly coupled to the fuel tank configured for distributing fuel from the fuel tank throughout the fuel system, and a second pump fluidly coupled to the first pump by a pressure regulating valve and configured for driving fuel to an engine.

A fluid flow system includes a main valve having a spool, a first chamber, and a second chamber. A pressure difference between the first chamber and the second chamber is configured to move the spool to control fluid flow. An electromechanical meter interface device (EMID) is in fluid communication with at least one of the first and second chambers of the main valve. The EMID is configured to meter fluid from a first source and a second source to the at least one of the first chamber and the second chamber. The first source has a different pressure from the second source. A fixed orifice is arranged between the main valve and the EMID. A fuel system for a gas turbine engine is also disclosed.

A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.

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 combustion-gas supply system and a combustion-gas supply method thereof, a device equipped with a turbine engine, and a fracturing system are provided. The combustion-gas supply system includes a main pipeline and a multi-functional pipeline; the main pipeline includes a first sub-pipeline and a second sub-pipeline; the first sub-pipeline includes a first gas intake pipe, a first gas supply valve and a first gas outlet pipe arranged in sequence; the second sub-pipeline includes a combustion-gas supply valve and a gas supply pipe, the first gas outlet pipe is connected with the combustion-gas supply valve, the gas supply pipe is configured to be connected with a turbine engine, the multi-functional pipeline includes a second gas intake pipe, a second gas supply valve and a second gas outlet pipe arranged in sequence, and the second gas outlet pipe is communicated with the first gas outlet pipe.

A passive flow splitting system for use in a turbine engine control system to provide split fuel flow to two fuel manifolds to supply primary and secondary fuel injectors for the particular combustion zones thereof utilizing intentionally different split ratios dependent on ascending or descending combustion fuel flow is provided. The system includes a passive fuel divider valve (FDV) that includes a primary piston and a secondary piston. The primary piston is moveable independently from the secondary piston during a portion of its stroke, and is hydro-locked to the secondary piston during another portion of its stroke. An ecology valve is also provided to purge the fuel from the primary and/or secondary manifolds during different modes of operation. A transfer valve is included to control the position of ecology piston of the ecology valve.

A gas turbine engine shut-down system includes a pump configured to draw a flow of fuel from a source, a fuel nozzle configured to receive the flow of fuel from the pump, a fuel shut-off valve in fluid communication with the pump, a recirculation circuit for circulating excess fuel to a location upstream of the pump; a solenoid valve in communication with the pump and the recirculation circuit; and a fuel-bypass valve. The fuel-bypass valve includes a first opening connected to the fuel pump, a second opening connected to the fuel shut-off valve, a third opening connected to the recirculation circuit, a fourth opening connected to the solenoid valve, and a piston disposed within the fuel-bypass valve and movable between a plurality of positions.

The invention may be embodied a valve for a combustor of a gas turbine, the valve including: a housing including a fluid inlet and fluid outlets; an actuator within the housing and movable between an open position and a closed position; a fluid path through the housing between the fluid inlet and the fluid outlets, wherein the fluid path is blocked while the actuator is in the closed positions such that fluid may not flow from the inlet to the outlets and fluid may not flow between the outlets, and wherein one of the fluid outlets is fluidly connected to a first combustion can of the combustor, and another of the fluid outlets is fluidly connected to a second combustion can of the combustor.

A direct-fired gas turbine heater comprises a gas turbine engine, a main blower that receives cold air from the ambient, a mixing plenum that receives cold air from the main blower and hot gas from the turbine and delivers warm air, an air blower plenum that that receives cold air from the main air blower and delivers air to the mixing plenum, and an air intake plenum that receives cold air from the ambient and the air blower plenum and delivers cold air to a turbine compressor, an air intake valve, and an air starter valve. The gas turbine engine comprises the compressor that receives cold air, a fuel manifold that receives combustible fuel, a combustor that receives compressed air from the compressor and fuel from the fuel manifold, a turbine that receives hot gas from the combustor, and a shaft connecting the compressor and turbine.