Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Materials Corporation

Hitachi Metals, Ltd.

National Institute for Materials Science

Yoshitaka Uemura

Ikuo Okada

Masahiko Mega

Hidetaka Oguma

Daisuke Yoshida

Shinya Imano

Kazutaka Mori

Taiji Torigoe

Masamitsu Kuwabara

Yuting Wang

Keizo Tsukagoshi

Ichiro Nagano

Yoshifumi Okajima

Norihiko Motoyama

Shigenobu Eguchi

Takanori Matsui

Takanao Komaki

Satoshi Hada

Satoshi Mizukami

Junichiro Masada

Masaki Taneike

Saki Matsuo

Komei Kato

Takuya Murai

Sachio Shimohata

Naotoshi Okaya

Yasumasa Kunisada

Ryozo Tamura

Ryota Okimoto

Hiroshi Harada

Yoshiaki Inoue

Hiroyuki Kimura

Eisaku Ito

Tadashi Fukuda

Koji Takahashi

Shunsuke Torii

Shuji Tanigawa

Toshiharu Kobayashi

Hideaki Kaneko

Yutaka Koizumi

Kengo Yamaguchi

Kosuke Fujiwara

Minoru Ohara

Tadaharu Yokokawa

Kyoko Kawagishi

Ikumasa Koshiro

Yasuhiko Tsuru

Yoshiyuki Inoue

Shigenari Horie

Masato Shida

Daisuke Kudo

Ken Fujita

Toshihiko Tsunatani

Masato Itoh

Kenichi Yaguchi

Masao Sakamoto

Tetsuji Kawakami

Masaya Kanikawa

Michinari Yuyama

Shusuke Sakuma

Rumi Haruna

Syuho Tsubota

A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.

Turbine blade

A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.

Turbine blade and method for manufacturing the turbine blade

There is provided an additive manufactured (AM) article formed of a Co based alloy having a composition comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 30% or less in total of Fe and Ni, the Fe being 5% or less; 5-12% in total of W and/or Mo; 0.5-2% in total of Ti, Zr, Nb and Ta; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The AM article comprises crystal grains with an average size of 10-100 &#x3bc;m. In the crystal grains, segregation cells with an average size of 0.15-1.5 &#x3bc;m are formed, in which components constituting an MC type carbide phase comprising the Ti, Zr, Nb and/or Ta are segregated in boundary regions of the cells, and/or grains of the MC type carbide phase are precipitated at an average intergrain distance of 0.15-1.5 &#x3bc;m.

Cobalt based alloy additive manufactured article, cobalt based alloy product, and method for manufacturing same

A slurry for forming a mold includes a silica sol as a dispersion medium and niobia-stabilized zirconia dispersed in the silica sol.

Slurry for forming mold, mold and method for producing mold

A method for manufacturing a core (S) includes: a coating step (S) of adding an organic binder to a large particle group composed of silica-containing large particles, and coating surfaces of the large particles with the organic binder; a mixing step (S) of mixing, after the coating step (S), the large particle group and a small particle group composed of silica-containing small particles having a smaller particle size than the large particles; a laminate shaping step (S) of forming, after the mixing step (S), a molding in which a mixture of the large and small particle groups is used; and a sintering step (S) of sintering the molding after the laminate shaping step (S).

Method for manufacturing core, and method for manufacturing turbine member in which core is acquired by said core manufacturing method

A Ni-based alloy comprises nitrides, of which an estimated largest size is an area-equivalent diameter of 12 &#x3bc;m to 25 &#x3bc;m, the estimated largest size of the nitrides being determined by calculating an area-equivalent diameter D which is defined as D=Ain relation to an area A of a nitride with a largest size among nitrides present in a measurement field of view area Sof an observation of the Ni-based alloy, repeatedly performing this operation for n times corresponding to a measurement field of view number n to acquire n pieces of data of the area-equivalent diameter D, arranging the pieces of data of area-equivalent diameter D in ascending order into D, D, . . . Dto calculate a standardized variable y, plotting the area-equivalent diameter D and the standardized variable yon X and Y axes of an X-Y coordinate system, respectively, to obtain a regression line y=a&#xd7;D+b (wherein a and b are constants) to calculating ywhere a cross-sectional area to be predicted S is 100 mm, and substituting the obtained value of yinto the regression line to obtain the estimated largest size of the nitrides.

Ni-based alloy, ni-based alloy for gas turbine combustor, member for gas turbine combustor, liner member, transition piece member, liner, and transition piece

A method for producing a thermal spray powder includes: a preparing step of preparing a powder mixture containing a first particle made from zirconia-based ceramic containing a first additive agent and a second particle made from zirconia-based ceramic containing a second additive agent, the powder mixture having a 10% cumulative particle diameter of more than 0 &#x3bc;m and not more than 10 &#x3bc;m; and a secondary-particle producing step of producing a plurality of secondary particles each of which includes the first particle and the second particle sintered with each other.

Method of producing thermal spray powder, manufacture apparatus of thermal spray powder, and thermal spray powder produced by the producing 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 object is to reduce changes in mechanical properties of a gas turbine blade base material during repair or regeneration of a gas turbine blade. For this purpose, a gas turbine blade after being operated is washed by being immersed into a strong alkaline washing solution, and the gas turbine blade after being washed with the strong alkaline washing solution is washed with water. The gas turbine blade after being washed with water is then washed by being immersed into a weak acid washing solution, and the gas turbine blade after being washed with the weak acid washing solution is subjected to heat treatment. The gas turbine blade after the heat treatment is then immersed into a strong acid washing solution, whereby the coating formed on the surface of the gas turbine blade is removed.

Method for regenerating gas turbine blade and gas turbine blade regenerating apparatus

A Ni-based heat resistant alloy for a gas turbine combustor, comprising a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.001 to 0.020%, C: 0.03 to 0.15%, and a balance consisting of Ni and unavoidable impurities, wherein a content of S and P contained in the unavoidable impurities is controlled to be, in mass %, S: 0.015% or less, and P: 0.015% or less, wherein the alloy has a texture in which MC type carbide and MC type carbide are uniformly dispersed in &#x3b3; phase matrix.

Nickel-based heat resistant alloy for gas turbine combustor

A wire for welding Ni-based heat resistant alloy, comprising: a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.0001 to 0.020%, C: 0.03 to 0.15%, and a balance of Ni and unavoidable impurities, wherein a content of S and P contained in the unavoidable impurities is controlled to be, in mass %, S: 0.004% or less, and P: 0.010% or less, wherein the wire has a texture in which MC type carbide and MC type carbide are uniformly dispersed in the matrix.

Wire for welding nickel based heat resistant alloy

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Yokohama, Japan

Yoshitaka Uemura