Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

National Institute for Materials Science

Mitsubishi Heavy Industries, Co., Ltd.

Mitsubishi Jukogyo Kabushiki Kaisha

Mitsubishi Power, Ltd.

Mitsubishi Heavy Indsutries, Ltd.

Keizo Tsukagoshi

Junichiro Masada

Satoshi Hada

Ikuo Okada

Taiji Torigoe

Yoshifumi Okajima

Yoshitaka Uemura

Masaki Taneike

Hidemichi Koyabu

Hiroshi Harada

Hideaki Sugishita

Eisaku Ito

Kazuo Uematsu

Sunao Aoki

Masahiko Mega

Toshiharu Kobayashi

Yutaka Koizumi

Hidetaka Oguma

Tadaharu Yokokawa

Kyoko Kawagishi

Tomoko Hashimoto

Masao Sakamoto

Masahiro Yamada

Yoshiaki Inoue

Satoshi Tanimura

Hidekazu Uehara

Hiroyuki Kimura

Kazutaka Mori

Tanehiro Shinohara

Hiroyuki Yamazaki

Shinya Ishikawa

Masamitsu Kuwabara

Hitoshi Morimoto

Masanori Yuri

Koji Takahashi

Shunsuke Torii

Shuji Tanigawa

Katsuhiko Abe

Ichiro Nagano

Yukihiro Hashimoto

Hideaki Kaneko

Ichiro Fukue

Kunihiko Waki

Saki Matsuo

Masato Araki

Kazumasa Takata

Yasuhiko Tsuru

Yoshiaki Nishimura

Shigenari Horie

Sachio Shimohata

Daisuke Kudo

Naotoshi Okaya

Toshio Sakon

Tatsuji Takahashi

Hiroji Tada

Ryota Okimoto

Soji Kasumi

Michinari Yuyama

Masao Terazaki

Masahiko Mori

Hidataka Oguma

Takeshi Naito

Jyunichiro Masada

Provided is a high-strength, heat-resistant, Ni-base alloy comprising Co: from 5 to 12%, Cr: from 5 to 12%, Mo: from 0.5 to 3.0%, W: from 3.0 to 6.0%, Al: from 5.5 to 7.2%, Ti: from 1.0 to 3.0%, Ta: from 1.5 to 6.0%, Re: from 0 to 2.0%, and C: from 0.01 to 0.20%. The high-strength, heat-resistant, Ni-base alloy is constituted of a Ni-based alloy, the balance of the Ni-based alloy comprising Ni and inevitable impurities. The density of the high-strength, heat-resistant Ni-base alloy is less than 8.5 g/cm.

High-strength, heat-resistant Ni-base alloy, method for producing same, and gas turbine blade

An insert assembly () includes an insert (), a reinforcing member (), and a retaining member (). The insert () is fixed to an end of an airfoil body () on one side in a radial direction. The reinforcing member () is disposed adjacent to an end of the insert () on the other side in the radial direction and enhances the rigidity of the insert (). The retaining member () is fixed to an end of the airfoil body () on the other side in the radial direction, and allows the insert () to be positioned relative to the airfoil body () in a direction orthogonal to the radial direction.

Insert assembly, airfoil, gas turbine, and airfoil manufacturing method

An erosion test apparatus includes a combustor configured to obtain a combustion gas by mixing and combusting compressed air and a fuel, and an erodent supply unit configured to supply an erodent to the combustion gas. The erosion test apparatus further includes an accommodation support unit configured to accommodate and support a test piece having a front surface coated through thermal barrier coating, and an accelerator configured to accelerate the combustion gas including the erodent to collide with the test piece.

Erosion test apparatus, accelerator and erosion test method

A process for producing a thermal barrier coating having an excellent thermal barrier effect and superior durability to thermal cycling. Also, a turbine member having a thermal barrier coating that has been formed using the production process, and a gas turbine. The process for producing a thermal barrier coating includes: forming a metal bonding layer () on a heat-resistant alloy substrate (), and forming a ceramic layer () on the metal bonding layer () by thermal spraying of thermal spray particles having a particle size distribution in which the 10% cumulative particle size is not less than 30 &#x3bc;m and not more than 100 &#x3bc;m.

Process for producing thermal barrier coating

Provided is a Ni-based single crystal superalloy containing

Ni-based single crystal superalloy

An inner wall surface of a low-pressure-side side plate opposite to a lateral surface of a thin plate is formed along a direction crossing an axial direction of a rotating shaft such that a gap between the inner wall surface and the thin plate gradually decreases from a radially inner side toward a radially outer side of the low-pressure-side side plate.

Shaft seal mechanism

The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass,

An airfoil part includes a plurality of cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.

Turbine vane and gas turbine

In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the main body of the segment body; a first cavity that receives the cooling air from the cooling space; and a first cooling passage, of which one end communicates with the first cavity, and the other end blows out the cooling air from openings that are arranged in the side end portion into combustion gas; the openings of the first cooling passages being arranged so that the arrangement pitch of the openings becomes smaller or the opening area of the openings becomes larger on the upstream in the flow direction of the combustion gas than the openings on the downstream, and are arranged so that the arrangement pitch of the openings becomes larger or the opening area of the openings becomes smaller on the downstream in the flow direction of the combustion gas than the openings on the upstream.

Cooling system of ring segment and gas turbine

A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region and a second region having a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages.

Provided is a turbine blade structure that is capable of suppressing quality variations of cast products during the manufacturing of turbine blades. A turbine blade structure wherein the space inside an air foil is divided into a plurality of cavities, partitioned by rib members provided substantially perpendicular to the center line connecting a leading edge and a trailing edge, is provided with partition members that partition the inside of the cavities located in the central portion of the blade, excluding the blade leading-edge side and the blade trailing-edge side, into blade pressure side cavities and blade suction side cavities substantially along the center line, wherein blade leading-edge end portions and blade trailing-edge end portions of the partition members are inserted from one shroud surface side to the other shroud surface side along engagement grooves formed on the rib members.

Turbine blade structure

In a specimen collecting method according to the present invention, a specimen is collected from a surface () of a blade. An ultrasonic cutter having a cylindrical cutting blade is fed from the surface () of the blade to a surface () of a base material (), and thus, a cylindrical incision is formed. After performing cutting to expand the incision outwardly, a rotating cutter () having a disc-shaped cutting blade () performs cutting inwardly from the cylindrical incision. Thus, a part () situated inside the incision is cut away. The part () becomes the specimen.

Specimen collecting method and blade temperature estimating method

In a turbine blade in which a tabular rib partitioning the blade into a pressure side and a suction side is provided in substantially the midsection of the blade along a center line connecting a leading edge and a trailing edge, and at least two cavities of which a cavity at the suction side and a cavity at the pressure side do not communicate with each other are provided, a pressure adjustment member for cooling air flowing into and out of the cavity at the suction side reduces the amount of cooling air flowing into the suction side, relative to the pressure side.

Turbine blade

A combined cycle system includes a gas turbine ( ) having a generator ( ), a compressor ( ), a combustor ( ), a blade cooling air cooler ( ), a fan ( ), and a turbine ( ); a steam turbine ( ) having a high pressure turbine ( ), an intermediate pressure turbine ( ), and a low pressure turbine ( ); and a waste heat recovery boiler ( ). Saturated water from a high pressure pump ( ) is partially led into a heat exchanger ( ) for cooling steam to be supplied into a moving blade ( ) and a stationary blade ( ). Also, outlet steam from the high pressure turbine ( ) is led into the moving blade ( ), the stationary blade ( ), and the combustor transition piece ( ) for cooling thereof, and the steam is then supplied to an inlet of the intermediate pressure turbine ( ). Further, the outlet steam from the high pressure turbine ( ) is led into the turbine ( ) for cooling blades thereof. The steam used for cooling the stationary blade is supplied to the inlet of the intermediate pressure turbine ( ), and the steam used for cooling the moving blade is supplied to a reheater ( ). Thus, the efficiency is enhanced.

Steam cooled gas turbine system with regenerative heat exchange

Growing community of inventors

Tokyo, Japan

Keizo Tsukagoshi