Hitachi, Ltd.

Tsuyoshi Takano

Shinya Marushima

Manabu Matsumoto

Yasuo Takahashi

Masami Noda

Nobuaki Kizuka

Shinichi Higuchi

Shunichi Anzai

Ryou Akiyama

Hiroyuki Doi

Akira Yoshinari

Hideki Tamaki

Akira Okayama

A Ni-based alloy hardened with the &#x3b3;' phase, which is able to exhibit not only superior strength at high temperatures, but also excellent hot corrosion resistance and oxidation resistance at high temperatures in spite of containing no Re or reducing the amount of Re. The Ni-based superalloy contains, by weight, C: 0.01 to 0.5%, B: 0.01 to 0.04%, Hf: 0.1 to 2.5%, Co: 0.8 to 15%, Ta: more than 0% but less than 8.5%, Cr: 1.5 to 16%, Mo: more than 0% but less than 1.0%, W: 5 to 14%, Ti: 0.1 to 4.75%, Al: 2.5 to 7%, Nb: more than 0% but less than 4%, V: 0 to less than 1.0%, Zr: 0 to less than 0.1%, Re: 0 to less than 9%, at least one of platinum group elements: 0 to less than 0.5% in total, at least one of rare earth elements: 0 to less than 0.1% in total, and the rest being Ni except for unavoidable impurities.

Ni-based superalloy having high oxidation resistance and gas turbine part

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 turbine rotor can fix the heat resisting pipes provided in divided form per the disk member with simple structure for preventing wearing and damaging. The turbine rotor includes a coolant flow path formed through a plurality of disc shaped members respectively stacked across stacking planes in axial direction, a heat resisting pipe divided into a plurality of fractions adapted to be inserted into a portion of the coolant flow path defined in each disc shaped member, spot facing recesses each formed at opening portion of coolant flow path at the same side of the disc shaped member coaxially with the coolant flow path and having greater inner diameter than the opening portion, and ring shaped projecting portions formed at respective end portions of the fractions of the heat resisting pipe and engageable with respective spot facing recesses.

Turbine rotor

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

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.

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.

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Hitachi, Japan

Tsuyoshi Takano