Hitachi, Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Nobuaki Kizuka

Shinya Marushima

Masami Noda

Yasuhiro Horiuchi

Shinichi Higuchi

Manabu Matsumoto

Hidetaro Murata

Hidetoshi Kuroki

Shunichi Anzai

Takanori Shibata

Kenji Nanataki

Tsuyoshi Takano

Tomomi Koganezawa

Nobuhiro Seiki

Ryou Akiyama

Atsushi Sano

Ryo Kawai

Kazuhiko Kawaike

Takashi Ikeguchi

Hidefumi Araki

Masaru Sekihara

Hironori Tsukidate

Takeo Saito

Shigeo Hanamiya

Shin'ichi Higuchi

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 bladescircumferentially mounted to an inner circumferential surface side of a casingforming a annular path; and an inner barrelsupported 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 shroudmounted to an inner circumferential surface of the casing at a position facing the inner barrel, and an inner shroudsupporting 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, the inner shroudand the blade portionsare formed in a monolithic structure by milling.

Compressor

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.

Method for starting premixed combustion in combustor for two-shaft gas turbine

Provided is a member having an internal cooling passageformed therein and having opposed partition wallsbetween which a medium flows to cool a parent material, including a first heat transfer ribwhich extends from almost the center between the opposed partition wallsto one partition walland slants in a downstream direction of the medium, and a second heat transfer ribwhich extends from almost the center between the opposed partition wallsto the other partition walland slants in the downstream direction of the medium, wherein a slitorwhich passes through between an upstream side of the cooling passageand a downstream side thereof is formed in the first heat transfer ribor the second heat transfer rib

Member having internal cooling passage

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.

Material having internal cooling passage and method for cooling material having internal cooling passage

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 .+&#x2212;.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.

Turbine blade

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 casingto a wheel space via a low-pressure turbine initial stage stator bladeand a diaphragm. An upstream side space seal portionis adapted to restrict and divide the upstream side space into an outer circumferential portionand an inner circumferential portionand to allow cooling air to the upstream side space outer circumferential portionto blow out into the upstream side space outer circumferential portion. Also, a downstream side space seal portionis adapted to restrict and divide the downstream side space into an outer circumferential portionand an inner circumferential portionand to allow cooling air to blow out into the downstream side space outer circumferential portion

Two-shaft gas turbine

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.

Gas turbine and gas turbine cooling method

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.

Gas turbine installation including a compressed air humidifier and method

The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.

Production process of gas turbine

In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades. The holes in the radial direction and the cooling air supply holes are interconnected and supply members covering the connections are installed. The cooling air after cooling the second stage moving blades is introduced into collection holes formed in the outer periphery of the spacer via the cooling air collection holes. The cooling air collection holes and collection holes are interconnected and collection members covering the connection are installed. To make the sum of minimum sectional areas of the respective paths of the second stage moving blades, smaller than the sum of minimum sectional areas of thee respective path of the first stage moving blades, a minimum sectional member is incorporated into the supply member.

Closed circuit blade-cooled turbine

A production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is initially set based on roughly set conditions, and the number of stages of the compressor and of the turbine for a desired cycle are set for the principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined to construct the gas turbine. When the set number of stages of the compressor or the turbine differs for a different desired cycle, a disk-shaped member having an outer periphery, which forms an inner peripheral wall of the annular flow passage of the compressor or the turbine, is assembled into the principal part having a smaller number of stages so that the bearing-to-bearing distance is kept constant.

In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades. The holes in the radial direction and the cooling air supply holes are interconnected and supply members covering the connection are installed. The cooling air after cooling the second stage moving blades is introduced into collection holes formed in the outer periphery of the spacer via the cooling air collection holes. The cooling air collection holes and collection holes are interconnected and collection members covering the connection are installed. To make the sum of minimum sectional areas of the respective paths of the second stage moving blades smaller than the sum of minimum sectional areas of the respective paths of the first stage moving blades, a minimum sectional member is incorporated into the supply member.

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Hitachinaka, Japan

Nobuaki Kizuka