A system for controlling a turbine valve is provided. The system includes a hydraulic pilot valve section being moveable in a first direction and a second direction; a main hydraulic valve section being moveable in a first direction to close the turbine valve and a second direction to open the turbine valve; a position demand indicating a desired position of the turbine valve; a first feedback indicating an actual position of the hydraulic pilot valve section; and aa second feedback indicating an actual position of the main hydraulic valve section. The system also includes a pilot valve error; a main valve error; a turbine valve error; and a pilot valve adjustment moving the hydraulic pilot valve section in response to the turbine valve error. The turbine valve error is repeatedly determined and the pilot valve adjustment repeatedly moves the hydraulic pilot valve section to minimize the turbine valve error.

A turbine control system is provided for decreasing the response time between readings of the speed of the turbine and changing a valve position in response thereto. The speed control system includes a speed probe that detects the speed of the turbine and a turbine valve that controls the flow of fluid or gas from or to the turbine. A controller receives a speed signal from the speed probe and sends valve position commands to the turbine valve. The controller also sends support functions to the turbine valve. The controller sends the valve position commands at a faster rate than the support functions.

A two-shaft gas turbine control system and method are provided that can enhance the efficiency and reliability thereof by controlling the amount of intake air spray and the rotational speed of a high-pressure turbine in accordance with the aperture of an inlet guide vane in a state where a two-shaft gas turbine is being operated with the efficiency of its compressor reduced. The control system includes a droplet spray device for spraying droplets to intake air for the compressor and a controller. The controller includes a fuel control section for adjusting a flow rate of the fuel to be supplied to the combustor, a spray flow rate control section for adjusting a flow rate of spray water to be supplied to the droplet spray device, an inlet guide vane aperture control section for adjusting the aperture of the inlet guide vane, and an efficiency improvement control section for outputting a command signal for bringing a balance between driving force for the compressor and power output of the high-pressure turbine to the fuel control section, the spray flow rate control section and the inlet guide aperture control section. In response to the commands from the improvement control section, the controller reduces the rotational speed of the high-pressure turbine and controls the inlet guide vane so as to be more open, thereby appropriately controlling the flow rate of the spray water.

An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber outside a gas turbine and providing compressed air to the combustion chamber in order to carry out a combustion process supplemented with high pressure steam pulses.

The gas turbine comprises a compressor, a combustor, and a turbine. The method comprises: compressing air with the compressor and feeding compressed air continuously to the combustor, feeding fuel to the combustor, continuously firing the mixture of fuel and gas in the combustor, feeding combustion gases from the combustor to the turbine, and supplying at least a portion of the total amount of fuel that is supplied to the combustor intermittently.

A gas turbine having a wet compression device which allows droplets of an aqueous liquid mixture to be introduced into a compressor of the gas turbine during operation of the gas turbine, the aqueous liquid mixture containing at least one surfactant. The aqueous liquid mixture additionally contains at least a defoaming agent, and the gas turbine has a second metering device, which is designed to feed a predetermined quantity of defoaming agent into water which is provided for use in the wet compression device.

A method is provided during which an aircraft powerplant is provided. The aircraft powerplant includes a combustor and a water recovery system. The water recovery system includes a condenser and a reservoir. Fuel is combusted within the combustor to provide combustion products. Water is extracted from the combustion products using the condenser. The water recovery system is operated in one of a plurality of modes based on likelihood of contrail formation. The modes include a first mode and a second mode, where the water is collected within the reservoir during the first mode, and where the water passes through the water recovery system during the second mode.

The aim of the invention is to significantly increase the electrical efficiency or the proportion of the effective work of gas turbines, even in small gas turbines or microsize gas turbines having a simple design. According to the invention, the drawbacks of the prior art are overcome using wet combustion with oxygen, the oxygen being supplied via mixed-conducting ceramic membranes. The driving force needed for the oxygen to penetrate is created by lowering the partial pressure of the oxygen on the permeate side of the membrane module (5), and the energy required therefor is taken from the process energy produced in the gas turbine process.

An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine when generating power. The invention is based on the idea of arranging a combustion chamber (10) outside a turbine (22) and providing compressed air from serially connected compressors to an air chamber in which the air is heated and then exhausted to the combustion chamber in order to carry out a combustion process supplemented with high pressure steam pulses.

The present embodiments disclose a method of running an air inlet system upstream of one or more inlet air filters of a device protected by air filtration, wherein the method comprises: regulating the relative air humidity of the inlet air at the one or more inlet air filters in dependence of the inlet air filters differential pressure.