Hitachi, Ltd.

Nippon Telegraph and Telephone Corporation

Nippon Telephone and Telegraph Corporation

Hitachi Service Engineering Co., Ltd.

Hitachi Service Engineering, Ltd.

Manabu Matsumoto

Shinya Marushima

Takashi Ikeguchi

Kazuhiko Kawaike

Masaru Sekihara

Masami Noda

Tsuyoshi Takano

Takashi Machida

Tadasi Sonobe

Shunichi Anzai

Nobuaki Kizuka

Ryo Akiyama

Toshiaki Kobari

Shinjiroo Ueda

Toru Murashita

Ryou Akiyama

Mamoru Katane

Satoshi Ido

Kazuo Kuroishi

Shinjiro Ueda

Akinori Shibayama

Hiroaki Sakurabata

Nobuo Hirano

Shiro Matsuzaki

Takeshi Sakamoto

Nariyoshi Kobayashi

Shunji Kakiuchi

Takao Takahashi

Yoshiaki Kazawa

Toa Hayasaka

Toyoki Kitayama

Kazuo Kuroichi

Shin'ichi Higuchi

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

An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Coolant recovery type gas turbine

A turbine rotor includes a plurality of moving blades having cooling paths through which a refrigerant flows inside, a plurality of wheels having the moving blades mounted in the outer periphery thereof and at least one spacer member installed between the wheels. The spacer member has a plurality of flow paths through which a refrigerant flows after cooling the moving blades. The plurality of flow paths have flow paths interconnecting to the cooling paths in the moving blades on a first wheel adjacent the spacer member and interconnecting to a space formed on a side wall surface with which a second wheel adjacent the spacer member and the spacer member are in contact.

Gas turbine, gas turbine apparatus, and refrigerant collection method for gas turbine moving blades

A gas turbine having a rotor driven by a shaft with a cooling medium passageway therein has a heat shield pipe portion mounted inside the passageway which forms an air layer with a wall of the passageway to protect a bearing member metal supporting the shaft from the heat of a cooling medium and a seal shaft portion for forming a labyrinth seal to prevent leakage of the cooling medium are formed as one piece and constitute a heat shied seal pipe.

Gas turbine shaft and heat shield cooling arrangement

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.

A gas turbine having a rotor driver by a shaft with a cooling medium passageway therein has a heat shield pipe portion mounted inside the passageway which forms an air layer with a wall of the passageway to protect a bearing member metal supporting the shaft from the heat of a cooling medium and a seal shaft portion for forming a labyrinth seal to prevent leakage of the cooling medium are formed as one piece and constitute a heat shied seal pipe.

A turbine rotor comprises first and second wheels each having turbine blades fixed to a peripheral portion thereof, and a spacer arranged so as to be sandwiched between the first and second wheels, and is characterized in that in a partitioning member is provided between the spacer and at least one of the first and second wheels, coolant paths in which coolant for cooling the turbine blades flows are provided inside the turbine blades, and a cavity formed by the partitioning member and the spacer is provided in a recovery course through which the coolant passed through the coolant paths is exhausted from the turbine blades. A gas turbine comprising the turbine rotor as mentioned above and a cooling method of the turbine rotor are disclosed.

Turbine rotor, cooling method of turbine blades of the rotor and gas turbine with the rotor

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 and to prevent the cooling air from leaking into the junction, the holes in the radial direction and the cooling air supply holes are interconnected and the supply members covering the junction are fit into them. The cooling air after cooling the second stage moving blades is introduced into the collection holes formed in the outer periphery of the spacer via the cooling air collection holes and to prevent the cooling air from leaking into the boundary, the cooling air collection holes and collection holes are interconnected and the collection members covering the boundary are fit into them. 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.

A gas turbine having a structure for collecting a refrigerant after cooling the moving blades, has a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant flows after cooling the moving blades are provided in the spacer members. First flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.

A gas turbine has a rotor shaft which includes a plurality of discs, each having a plurality of moving blades driven by combustion gas and arranged annularly on the peripheral portion and having spaces arranged between the discs. The respective discs and spacers are arranged in the axial direction. Gap portions are formed between the rotor axis side regions of the discs facing the spacers and adjacent spacers. Contact surfaces contacting each other on both rotor peripheral side regions of the discs facing the spaces and adjacent spacers are formed. A first flow path for supplying a coolant into the moving blades and a second flow path for recovering the coolant heated by the moving blades from the moving blade are provided. A third flow path for introducing fluid into the gap portions is formed in the discs with the third flow path being independent from the first and second flow paths.

Operational reliability of a gas turbine is improved by suppressing the thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs. Gap portions are formed between a region on the rotor shaft center portion side of the discs facing the spacers and spacers adjacent thereof. Contact surfaces are formed which contact on both a region on the rotor peripheral side of the discs facing the spacers and adjacent spacers thereto. Furthermore, a third flow path leading fluid to the above-mentioned gap portions is provided.

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Ibaraki-machi, Japan

Manabu Matsumoto