Abstract: A gas turbine includes a compressor, a combustor, a turbine, a generator, and a control apparatus, the compressor being provided with an air extraction valves, a plurality of inlet guide vanes, and a plurality of casing air extraction valves at its last stage, in which the control is carried out on at least one of the opening of the air extraction valve, the opening of the inlet guide vanes, and the number of openings of the casing air extraction valves which are defined as control parameters taking blade vibration stress values as indexes based on a compressor metal temperature included in behavior parameters of the gas turbine.

Abstract: A gas turbine includes a compressor, a combustor, a turbine, a generator, and a control apparatus, the compressor being provided with an air extraction valves, a plurality of inlet guide vanes, and a plurality of casing air extraction valves at its last stage, in which the control is carried out on at least one of the opening of the air extraction valve, the opening of the inlet guide vanes, and the number of openings of the casing air extraction valves which are defined as control parameters taking blade vibration stress values as indexes based on a compressor metal temperature included in behavior parameters of the gas turbine.

Abstract: An exhaust frame includes: an inner casing; an inner diffuser which defines, between the inner diffuser and the inner casing, an annular inner cooling passage connected to a final-stage wheel space; an outer diffuser which defines an exhaust passage between the outer diffuser and the inner diffuser; an outer casing which defines an annular outer cooling passage between the outer casing and the outer diffuser; a strut which connects the inner casing and the outer casing to each other while crossing the exhaust passage; a strut cover which connects the inner diffuser and the outer diffuser to each other, and defines, between the strut cover and the strut, an annular connection passage connecting the inner cooling passage and the outer cooling passage to each other; and a communication hole provided in a wall of the outer cooling passage at a position on the downstream side of a center line of the strut in the flow direction of a combustion gas.

Abstract: A two-shaft gas turbine of the present invention, in which a mass flow of an air into a compressor is regulated by controlling a set angle of an inlet guide vane (IGV) on an air intake side of the compressor, comprises, as a device to control the set angle of the IGV, a first controller to control the set angle of the IGV based on a corrected speed of the gas generator shaft during low speed rotation of the gas generator shaft, the corrected speed having been corrected according to an ambient temperature; a second controller to control the set angle of the IGV to maintain a constant actual speed of the gas generator shaft during high speed rotation of the gas generator shaft; and an ambient temperature correction part to increase the actual speed maintained constant by the second controller if the ambient temperature is equal to or more than a threshold value.

Abstract: A 2-shaft gas turbine has a controller which controls the opening degree of an air inlet guide vane to adjust the inlet mass flow rate to a compressor. The air inlet guide vane control unit includes a first control unit that adjusts the opening degree of the inlet guide vane to keep the speed of a high pressure turbine shaft constant; a control status confirmation unit that confirms the actual speed and the opening degree of the inlet guide vane; and a low ambient temperature correction unit that reduces the actual speed in a case where the actual speed is equal to or greater than a predetermined threshold value, the opening degree of the inlet guide vane is equal to or greater than a predetermined threshold value, and the ambient temperature is equal to or less than a predetermined threshold value.

Abstract: A twin-shaft gas turbine can be used for 50 and 60 Hz power generation without using a reducer. A gas generator includes a compressor that generates compressed air, a burner that burns a fuel mixed with the compressed air received from the compressor so as to generate combustion gas, and a high-pressure turbine that is rotationally driven by the combustion gas received from the burner and generates driving force for the compressor. An output turbine includes a low-pressure turbine that is driven by exhaust gas received from the high-pressure turbine and a power generator that is driven by the low-pressure turbine. A control device reduces opening degree of IGV of the compressor and thereby reduces power of the compressor, and the rotational frequency of the gas generator is increased in a full-speed no-load operating state of the power generator.

Abstract: A 2-shaft gas turbine has a controller which controls the opening degree of an air inlet guide vane to adjust the inlet mass flow rate to a compressor. The air inlet guide vane control unit includes a first control unit that adjusts the opening degree of the inlet guide vane to keep the speed of a high pressure turbine shaft constant; a control status confirmation unit that confirms the actual speed and the opening degree of the inlet guide vane; and a low ambient temperature correction unit that reduces the actual speed in a case where the actual speed is equal to or greater than a predetermined threshold value, the opening degree of the inlet guide vane is equal to or greater than a predetermined threshold value, and the ambient temperature is equal to or less than a predetermined threshold value.

Abstract: An exhaust frame includes: an inner casing; an inner diffuser which defines, between the inner diffuser and the inner casing, an annular inner cooling passage connected to a final-stage wheel space; an outer diffuser which defines an exhaust passage between the outer diffuser and the inner diffuser; an outer casing which defines an annular outer cooling passage between the outer casing and the outer diffuser; a strut which connects the inner casing and the outer casing to each other while crossing the exhaust passage; a strut cover which connects the inner diffuser and the outer diffuser to each other, and defines, between the strut cover and the strut, an annular connection passage connecting the inner cooling passage and the outer cooling passage to each other; and a communication hole provided in a wall of the outer cooling passage at a position on the downstream side of a center line of the strut in the flow direction of a combustion gas.

Abstract: A gas turbine includes a disk wheel forming a rotor; a rotor blade including a shank mounted on the outer circumference of the disk wheel and a rotor blade profile portion; a stator blade including a stator blade profile portion and an inner circumferential end wall provided on the inner circumferential side of the stator blade profile portion; and a seal fin provided on the shank of the rotor blade so as to face an inside-diameter surface of the inner circumferential end wall of the stator blade. An abradable coating is applied to such a portion of the inside-diameter surface of the inner circumferential end wall of the stator blade that faces the seal fin.

Abstract: A two-shaft gas turbine of the present invention, in which a mass flow of an air into a compressor is regulated by controlling a set angle of an inlet guide vane (IGV) on an air intake side of the compressor, comprises, as a device to control the set angle of the IGV, a first controller to control the set angle of the IGV based on a corrected speed of the gas generator shaft during low speed rotation of the gas generator shaft, the corrected speed having been corrected according to an ambient temperature; a second controller to control the set angle of the IGV to maintain a constant actual speed of the gas generator shaft during high speed rotation of the gas generator shaft; and an ambient temperature correction part to increase the actual speed maintained constant by the second controller if the ambient temperature is equal to or more than a threshold value.

Abstract: A two-shaft gas turbine is provided that can raise an inlet temperature of a high-pressure turbine and the air quantity of a compressor to respective rated values at any atmospheric temperature without using a variable stator vane in the initial stage of a low-pressure turbine. The two-shaft gas turbine includes a power generator 21 having a compressor 11, a combustor 12 and a high-pressure turbine 13; a low-pressure turbine 14 driven by exhaust gas from the high-pressure turbine 13; a generator motor 23 connected to the gas generator 21; and a control unit 24. When either one of a value of the inlet temperature of the high-pressure turbine 13 and a value of the air quantity of the compressor 11 reaches a rated value before the other value reaches a rated value, the control unit 24 drives the generator motor 23 to bring the other value close to the rated value.

Abstract: A gas turbine includes a disk wheel forming a rotor; a rotor blade including a shank mounted on the outer circumference of the disk wheel and a rotor blade profile portion; a stator blade including a stator blade profile portion and an inner circumferential end wall provided on the inner circumferential side of the stator blade profile portion; and a seal fin provided on the shank of the rotor blade so as to face an inside-diameter surface of the inner circumferential end wall of the stator blade. An abradable coating is applied to such a portion of the inside-diameter surface of the inner circumferential end wall of the stator blade that faces the seal fin.

Abstract: A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out.

Abstract: An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vane root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of ±2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates, wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion.

Abstract: A twin-shaft gas turbine, which has a gas generator including a compressor, a combustor, and a high-pressure turbine, is configured to make a first control mode and a second control mode selectively useable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

Abstract: An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vane root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of .+?.2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion.

Abstract: A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively useable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

Abstract: A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively usable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

Abstract: The temperature rise of a wheel space between a high-pressure turbine and a low-pressure turbine is suppressed. Cooling air is led from outside a casing 17 to a wheel space via a low-pressure turbine initial stage stator blade 5 and a diaphragm 11. An upstream side space seal portion 41 is adapted to restrict and divide the upstream side space into an outer circumferential portion 25 and an inner circumferential portion 27 and to allow cooling air to the upstream side space outer circumferential portion 27 to blow out into the upstream side space outer circumferential portion 25. Also, a downstream side space seal portion 42 is adapted to restrict and divide the downstream side space into an outer circumferential portion 26 and an inner circumferential portion 28 and to allow cooling air to blow out into the downstream side space outer circumferential portion 26.

Abstract: Provided are a combustor control method and a combustor controller capable of calculating the combustion air flow and the fuel flow in multi-shafts gas turbine with high precision and without the need of performing complicated calculations and thereby calculating a fuel-air ratio necessary for stable combustion control. The multi-shaft gas turbine is made up of a gas generator turbine and a power turbine. Combustors includes a diffusive combustion units and a plurality of premixed combustion units.