Abstract: It is an object of the present invention to provide a compressor that has a simple structure, produces a damping effect and improves aerodynamic performance. In a compressor including stator blades 4 circumferentially mounted to an inner circumferential surface side of a casing 6 forming a annular path; and an inner barrel 7 supported by the casing and arranged on the radially inside of the stator blade as a partition wall on the radial side of the annular path; the stator blade includes an outer shroud 10 mounted to an inner circumferential surface of the casing at a position facing the inner barrel, and an inner shroud 11 supporting a blade portion at an inner diameter side, the inner shroud being disposed in an annular groove formed in an outer circumferential surface of the inner barrel facing the inner shroud. The stator blade including the outer shroud 10, the inner shroud 11 and the blade portions 9 are formed in a monolithic structure by milling.

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: Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a which extends from almost the center between the opposed partition walls 6b, 6c to one partition wall 6c and slants in a downstream direction of the medium, and a second heat transfer rib 25b which extends from almost the center between the opposed partition walls 6b, 6c to the other partition wall 6b and slants in the downstream direction of the medium, wherein a slit 70a or 70b which passes through between an upstream side of the cooling passage 7c and a downstream side thereof is formed in the first heat transfer rib 70a or the second heat transfer rib 70b.

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 material having an internal cooling passage is provided which reduces a recirculation area to perform effective cooling. In the internal cooling passage formed in the material there is a wall surface provided with cooling ribs thereon to allow a cooling medium to flow along the wall surface, and the cooling ribs are arranged so that a portion of the cooling medium flowing in the vicinity of the center of the wall surface included in the cooling passage is allowed to flow toward both side edges of the wall surface and so that a portion of the cooling medium flowing on a surface of the cooling ribs moves to conform to the surface of the cooling ribs and flows to the wall surface.

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: 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: It is an object of the present invention to provide a compressor that has a simple structure, produces a damping effect and improves aerodynamic performance. In a compressor including stator blades 4 circumferentially mounted to an inner circumferential surface side of a casing 6 forming a annular path; and an inner barrel 7 supported by the casing and arranged on the radially inside of the stator blade as a partition wall on the radial side of the annular path; the stator blade includes an outer shroud 10 mounted to an inner circumferential surface of the casing at a position facing the inner barrel, and an inner shroud 11 supporting a blade portion at an inner diameter side, the inner shroud being disposed in an annular groove formed in an outer circumferential surface of the inner barrel facing the inner shroud. The stator blade including the outer shroud 10, the inner shroud 11 and the blade portions 9 are formed in a monolithic structure by milling.

Abstract: Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a which extends from almost the center between the opposed partition walls 6b, 6c to one partition wall 6c and slants in a downstream direction of the medium, and a second heat transfer rib 25b which extends from almost the center between the opposed partition walls 6b, 6c to the other partition wall 6b and slants in the downstream direction of the medium, wherein a slit 70a or 70b which passes through between an upstream side of the cooling passage 7c and a downstream side thereof is formed in the first heat transfer rib 70a or the second heat transfer rib 70b.

Abstract: Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a which extends from almost the center between the opposed partition walls 6b, 6c to one partition wall 6c and slants in a downstream direction of the medium, and a second heat transfer rib 25b which extends from almost the center between the opposed partition walls 6b, 6c to the other partition wall 6b and slants in the downstream direction of the medium, wherein a slit 70a or 70b which passes through between an upstream side of the cooling passage 7c and a downstream side thereof is formed in the first heat transfer rib 70a or the second heat transfer rib 70b.

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: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

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: 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: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: A gas turbine installation is provided in which turbine cooling air can be humidified with water while suppressing deterioration of the reliability of turbine blades. The gas turbine installation comprises a compressor for compressing air, a combustor for burning compressed air and fuel, a turbine driven by combustion gas, and a humidifier for humidifying the compressed air extracted from an intermediate stage or a discharge section of the compressor. The compressed air humidified by the humidifier is used as turbine cooling air. The humidifier includes a water distributor for adjusting an amount of water added to the compressed air.

Abstract: An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vain 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.