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.

A control system is provided for a turbine valve. The turbine valve has a first coil and a second coil to control or sense movement of a mechanical valve positioner. Two valve positioners are provided with each valve positioner having two drive circuits to drive the first and second coils. Switches are provided such that only one drive circuit is connected to each coil at a time. The control system may also include a hydraulic pilot valve section and a main hydraulic valve section. Feedbacks are used to determine a pilot valve error and a main valve error which are combined to determine a turbine valve error. The turbine valve error is repeatedly determined to minimize the error.

A turbine stator blade (21) includes a pressure side (21P) extending in a radial direction intersecting a flow direction of steam, and facing upstream in the flow direction. A slit (5) extending in the radial direction and capturing a liquefied component of the steam is formed on a downstream side of the pressure side (21P). A hydrophilic uneven region (6) having a liquid film capacity greater than that of the pressure side (21P) by being recessed in a depth direction intersecting the pressure side (21P) is formed in a further upstream position than the slit (5). The hydrophilic uneven region (6) has a depth in the depth direction increasing and a flow resistance decreasing toward downstream and toward the slit (5).

A turbine stator blade (21) includes a pressure side (21P) extending in a radial direction intersecting a flow direction of steam, and facing upstream in the flow direction. A slit (5) extending in the radial direction and capturing a liquefied component of the steam is formed on a downstream side of the pressure side (21P). A hydrophilic uneven region (6) having a liquid film capacity greater than that of the pressure side (21P) by being recessed in a depth direction intersecting the pressure side (21P) is formed in a further upstream position than the slit (5). The hydrophilic uneven region (6) has a depth in the depth direction increasing and a flow resistance decreasing toward downstream and toward the slit (5).

A breaker between two electrical circuits is provided that is closed when electrical properties in both of the electrical circuits are matching. Two check circuits are provided for comparing electrical properties of the two electrical circuits. Each of the check circuits sets a corresponding authorization to close the breaker. The breaker is only closed if both check circuits set an authorization to close the circuit.

A turbine speed probe diagnostic system is provided. The turbine includes a speed probe and a speed reading circuit. A speed lead connects the speed probe and speed reading circuit together to transmit speed signals from the speed probe to the speed reading circuit. A speed probe diagnostic circuit is also provided for connection to the speed lead. An isolation switch is provided to isolate the speed probe diagnostic circuit during normal operation when the speed reading circuit is receiving speed signals from the speed probe. When no speed signals are being received, the isolation switch closes and the speed probe diagnostic circuit performs a test on the speed probe or speed lead.

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.

A control system is provided for a turbine valve. The turbine valve has a first coil and a second coil to control or sense movement of a mechanical valve positioner. Two valve positioners are provided with each valve positioner having two drive circuits to drive the first and second coils. Switches are provided such that only one drive circuit is connected to each coil at a time. The control system may also include a hydraulic pilot valve section and a main hydraulic valve section. Feedbacks are used to determine a pilot valve error and a main valve error which are combined to determine a turbine valve error. The turbine valve error is repeatedly determined to minimize the error.

A steam turbine system (200) includes a steam turbine (60) in which a main flow path (C) through which a main steam flows is formed, and a saturated steam generation portion (210) that is configured to generate a saturated steam. The saturated steam generation portion (210) is configured to feed the saturated steam into a wet region (C1) in which the main steam in the main flow path (C) is in a wet state via a hollow portion formed inside a stator vane (650) of the steam turbine (60). The stator vane (650) has a plurality of supply ports that are formed such that the hollow portion is configured to communicate with the main flow path (C), and a discharge amount of the saturated steam increases from an inner circumferential side toward an outer circumferential side in a blade height direction.

A method for controlling a turbomachine including a temporary power-increasing device, the control method including a step wherein the flow rate of the coolant injected is adjusted as a function of the atmospheric pressure and/or of the ambient temperature and/or of at least one parameter such as the speed of rotation of a gas generator, the speed of rotation of a low-pressure turbine or of a power turbine, the gas pressure at the outlet of a compressor stage, the temperature at the inlet of the low-pressure turbine or of the power turbine, the engine torque, and/or the collective pitch of a helicopter rotor or the pitch of a propeller of a turboprop.