Hitachi, Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Heavy Industries Limited

Fujikura Limited

Mitsubishi Power, Ltd.

Yasuhiro Horiuchi

Makoto Takahashi

Shinya Marushima

Nobuaki Kizuka

Shinichi Higuchi

Hisato Tagawa

Masami Noda

Tetsuro Morisaki

Hidefumi Araki

Hidetoshi Kuroki

Yasuo Takahashi

Shigeo Hatamiya

Tomomi Koganezawa

Manabu Yagi

Hironori Tsukidate

Ryou Akiyama

Kunihiro Oga

Thanhlong Phan

Mutsumi Horitsugi

Hiroyuki Tate

Kenji Shingai

Takemitsu Miura

Singh Randeep

The present invention provides a gas turbine nozzle capable of reducing stress related to thermal elongation caused by a rise in gas turbine nozzle temperature and thus reducing stress produced when thermal deformation occurs in the gas turbine nozzle. The gas turbine nozzle according to the present invention includes nozzles formed integrally through an inner perimeter end wall and an outer perimeter end wall. The inner perimeter end wall has an upstream connection portion and a downstream connection portion. The upstream connection portion extends radially inward to be connected to an inner perimeter diaphragm. The downstream connection portion is located downstream from the upstream connection portion and extends radially inward to be connected to the inner perimeter diaphragm. The inner perimeter end wall has a thin-walled portion in a rear edge portion of the inner perimeter end wall, the thin-walled portion corresponding to a reduced wall thickness portion of the rear edge portion of the inner perimeter end wall.

Gas turbine nozzle

In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.

Gas turbine transition seal with hole through seal plate in groove of nozzle

The invention provides a gas turbine blade that is capable of reducing the temperature difference between the pressure side and the suction side even if the trailing-edge cooling channel is narrow, thereby lessening thermal stress as well. A gas turbine bladecomprises: an internal trailing-edge cooling channel formed by a suction-side cooling target surfaceand a pressure-side cooling target surfacethat face each other; and multiple vortex-generator-shaped finsdisposed between the two cooling target surfacesandsuch that the finsconnect the two cooling target surfacesand. Each of the vortex-generator-shaped finsincludes an oblique surfacelocated on the downstream side of the flow direction of a cooling medium. A normal lineto the oblique surfaceintersects with one of the two cooling target surfacesand

Gas turbine blade

A gas turbine airfoil is provided that is superior in the cooling performance of an end wall and in the thermal efficiency of a gas turbine. A gas turbine airfoil includes an airfoil portion having a cooling passage therein; and an end wall portion located at an inner band end portion of the airfoil portion in the turbine-radial direction. Cooling holes are disposed in the leading edge side hook portion of the end wall portion. The plurality of cooling holes are arranged at different distance of intervals in the circumferential direction of the gas turbine. Cooling air that has flowed in the cooling passage is configured to flow from the cooling holes toward the leading edge of the end wall portion.

Gas turbine airfoil

A gas turbine blade includes a hollow-blade-form portion formed by a leading edge on an upstream side of an working fluid of a gas turbine in a flow direction, a trailing edge on a downstream side of the working fluid in the flow direction, and a suction surface and a pressure surface reaching the trailing edge from the leading edge, and a shank portion for supporting the blade form portion. The blade also includes a partition for connecting the suction surface and the pressure surface in a hollow region of the blade-form portion, coolant paths formed by the partition, the suction surface, and the pressure surface, an impingement cooling hole formed in the partition for dividing the first path that is a flow path nearest to the leading edge side among the coolant paths and the second path adjacent to the first path, and first and second converter portions.

Gas turbine, gas turbine blade, and manufacturing method of gas turbine blade

There is provided a shroud structure for gas turbines capable of suppressing a drop in the amount of cooling air for cooling the inner shroud by reducing the amount of cooling air leakage that occurs along the cooling air path when feeding cooling air from the one-piece outer shroud to the inner shroud of the gas turbine and ensure more reliable cooling of the inner shroud. The gas turbine shroud structure contains a one-piece outer shroud, and an inner shroud retained on the inner circumferential side of the outer shroud in a structure divided into multiple inner shrouds along the periphery. An inner seal plate groove is formed on the outer circumference of the hook formed on the inner shroud, a seal plate is inserted in the inner seal plate groove, and the seal plate is mounted so that a section of the seal plate protrudes in the gap between the hook mechanism of the outer shroud and the inner shroud.

Shroud structure for gas turbine

Motive power supply equipment for a natural gas liquefaction plant includes gas turbine equipment having a compressor for compressing air, a combustor for generating combustion gases by burning a fuel and the compressed air from the compressor, and a turbine rotated by the combustion gases from the combustor. A low-temperature heat source supply system is provided which, during rated load operation of the gas turbine equipment, supplies carbon dioxide as a cooling medium to the gas turbine equipment in order to cool the gas turbine equipment. The carbon dioxide supplied is generated by separation from the natural gas in the natural gas purification equipment.

Natural gas liquefaction plant and motive power supply equipment for same

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

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

An advanced humid air turbine power plant capable of suppressing condensation of moisture in a cooling channel, which is provided to cool a high-temperature component of a gas turbine, in a start up stage, a coast down stage, and a load varying state of the gas turbine. In the advanced humid air turbine power plant comprising a compressed air supply line for supplying compressed air generated by a compressor to the high-temperature component of the gas turbine, and a humidified air supply line for supplying humidified air generated in a humidifying tower to the high-temperature component of the gas turbine, the power plant further comprises valves capable of adjusting respective air flow rates in the compressed air supply line and the humidified air supply line. A coolant is switched over from the compressed air to the humidified air in the start up stage and the load increasing stage of the gas turbine, and from the humidified air to the compressed air in the load decreasing stage and the coast down stage, as well as in the event of an abnormality in a humidifying line.

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Hitachinaka, Japan

Yasuhiro Horiuchi