Mitsubishi Heavy Industries Limited

Mitsubishi Power, Ltd.

Hidetaka Okui

Kentaro Suzuki

Ryosuke Mito

Shinya Hashimoto

Yoshifumi Okajima

Tatsuya Iwasaki

Akitomo Tsukahara

Kengo Shimojo

Kimiyasu Fujita

Daiki Yaguchi

Toshishige Ai

Kondo Takahiro

Based on a state of the gas turbine, either a normal start mode or a hot start mode is selected as a start mode. When startup control is started based on the start mode, the rotational speed of the gas turbine gradually increases. In a low rotational speed region, an opening degree of the inlet guide vane provided by a compressor is maintained at a first opening degree and a bleed valve is maintained at second opening degree. In a high rotational speed region, the inlet guide vane is controlled at first intermediate opening degree greater than the first opening degree and the bleed valve is controlled at a second intermediate opening degree less than the second opening degree. The first intermediate opening degree is set to be larger in the hot start mode. The second intermediate opening degree is set to be larger in the hot start mode.

Method for starting gas turbine

A gas turbine plant includes a gas turbine, a liquefaction facility capable of liquefying air, and a liquefaction controller. A compressor has an intake amount adjuster capable of adjusting an intake amount into a compressor casing. The liquefaction facility includes: a bleed line capable of bleeding compressed air from the compressor; a liquefaction system capable of liquefying the compressed air, a bleed amount adjustment valve; a return air line capable of guiding return air into a flow passage through which compressed air flows in the gas turbine; and a return amount adjusting valve. The liquefaction controller opens the bleed amount adjustment valve if an opening degree of the intake amount adjuster is a first opening degree, and opens the return amount adjusting valve if the opening degree of the intake amount adjuster is a second opening degree, which is an opening degree greater than the first opening degree.

Gas turbine plant, method for operating same, and method for modifying same

This control device for a gas turbine connected to a power generator capable of linking to a power system is configured to be able to switch operation modes of the gas turbine between a normal operation mode in which the gas turbine rotationally drives the power generator and a reverse power operation mode in which the gas turbine is rotationally driven by the power generator actuated as a motor by receiving power from the power system, the control device comprising: an index acquisition unit configured to acquire an index indicating the pressure ratio of a compressor of the gas turbine; and a signal output unit configured to output a signal for protecting the compressor when the index becomes less than a threshold value while the gas turbine is operating in the reverse power operation.

Control device for gas turbine, gas turbine facility, method for controlling gas turbine, and control program for gas turbine

A compressor control device includes: an inlet guide vane disposed in an inlet section of a compressor; a variable stationary blade disposed downstream of the inlet guide vane; a rotor blade disposed between the inlet guide vane and the variable stationary blade; a first actuator for adjusting a first opening degree of the inlet guide vane; a second actuator for adjusting a second opening degree of the variable stationary blade; a compressor inlet temperature detection part for detecting a compressor inlet temperature in the inlet section; and a control part for controlling the first actuator and the second actuator. The control part controls the first actuator and the second actuator such that an opening degree ratio of the first opening degree to the second opening degree increases as the compressor inlet temperature decreases, if the compressor inlet temperature is less than a threshold.

Compressor control device, control method for compressor, and control program product for compressor

A rotor has formed therein a groove with which a moving blade including a dovetail portion and a platform portion connecting the dovetail portion and a blade portion engages. The groove opens in a surface intersecting the axis of rotation of the rotor, and includes a contacting portion extending obliquely with respect to the axis of rotation and coming into contact with the dovetail portion, a bottom portion of an end portion on the radially inner side of the rotor, a joining portion between the contacting portion and the bottom portion, a platform facing portion facing the platform portion, and a chamfered portion formed on an end surface in the groove-extending direction. The chamfered dimension of the joining portion is greater on the side with an acute angle between the groove and the end surface than on the side with an obtuse angle between the groove and the end surface.

Rotor and compressor

The present invention includes a flow guide () that is disposed in a space (A) formed in a casing, on an outlet side of a diffuser (), the flow guide including: a first guide surface () that is disposed on a rotor side provided to a compressor and a gas turbine, and that delays turning of a flow direction of a compressed gas which has passed through the diffuser (); and a second guide surface () that is disposed outside the first guide surface () and that turns the flow direction of the compressed gas which has passed through the diffuser ().

Gas turbine

A stator vane body which is disposed in a flow path through which a working fluid flows and by which a clearance is formed between the stator vane body and an inner casing; a rotary shaft which is configured to rotate such that an angle of the stator vane body with respect to a flow direction of a main flow of the working fluid is varied; and a connection part which is configured to connect the stator vane body to the rotary shaft are provided. The connection part includes a first guide surface which is configured to guide the working fluid in a direction in which a flow direction of a leakage flow of the working fluid in the clearance which has flowed into toward a leading edge side of the stator vane body is directed in a flow direction of the main flow.

Variable stator vane and compressor

A gas turbine startup method and device wherein low-pressure, medium-pressure, and high-pressure air bleed flow paths supply compressed air bled from low-pressure, medium-pressure, and high-pressure air bleed chambers, respectively, of a compressor as cooling air to a turbine. Low-pressure, medium-pressure, and high-pressure exhaust flow paths discharge the compressed air in the low-pressure, medium-pressure, and high-pressure air bleed flow paths, respectively to the turbine exhaust system, and the low-pressure, the medium-pressure, and the high-pressure exhaust flow paths are provided respectively with a low-pressure exhaust valve, a medium-pressure exhaust valve, and a high-pressure exhaust valve. When the gas turbine starts up, the high-pressure exhaust valve is opened before the startup state of the gas turbine reaches a region in which rotation stall occurs.

Growing community of inventors

Yokohama, Japan

Hidetaka Okui