Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Masahiko Mega

Taiji Torigoe

Yoshifumi Okajima

Shuji Tanigawa

Yoshitaka Uemura

Minoru Ohara

Daisuke Kudo

Koji Tsukimoto

Naotoshi Okaya

Hiroki Komuro

Ken Fujita

Toshihiko Tsunatani

Yasushi Takeuchi

Ikuo Okada

Masamitsu Kuwabara

Keizo Tsukagoshi

Ichiro Nagano

Tomoaki Kitagawa

Yoshiaki Inoue

Hiroyuki Kimura

Eisaku Ito

Kazutaka Mori

Koichi Tanimoto

Koji Takahashi

Hiroyuki Mitsui

Junichiro Masada

Hideaki Kaneko

Kengo Yamaguchi

Masashi Kitamura

Takayuki Kurimura

Takahiro Tachibana

Atsushi Moriwaki

Mineaki Matsumoto

Yasuhiko Tsuru

Shigenari Horie

Masayuki Ota

Sachio Shimohata

Mitsuo Hasegawa

Hiroshi Makigano

Shingo Nakahara

Masahiko Onda

Takahisa Hasegawa

Kei Osawa

Masaya Kanikawa

Kimihiro Kishi

Seiji Katayama

Syuho Tsubota

Sosuke Kawasumi

Shusuke Sakuma

A ceramic coating according to at least one embodiment of the present disclosure includes: a bond coat layer formed on a substrate; and a ceramic layer formed on the bond coat layer. The ceramic layer has a first region in contact with an interface between the ceramic layer and the bond coat layer and a second region father away from the interface than the first region from the interface. In a cross-section along a thickness direction of the ceramic layer, the number of crack intersection points at which two or more cracks intersect per unit area in the ceramic layer is larger in the first region than in the second region.

Ceramic coating, turbine component, and gas turbine

A thermal barrier coating includes a bond coat layer deposited on a substrate, and a ceramic layer deposited on the bond coat layer. The ceramic layer includes a first layer having a porosity of 10% or more and 15% or less, and a second layer having a porosity of 0.5% or more and 9.0% or less and deposited on the first layer.

Thermal barrier coating, turbine member, gas turbine, and method for producing thermal barrier coating

A turbine rotor blade includes a blade body and a tip shroud on a tip of the blade body. The tip shroud has a contact block configured to face a tip shroud of an adjacent turbine rotor blade, and the contact block includes a base material, an oxidation resistant coating on the surface of the base material, and a hard wear resistant coating on the surface of the oxidation resistant coating.

Turbine rotor blade and contact surface manufacturing method

The present invention provides a thermal barrier coated component, monitoring or evaluation of the soundness of which is able to be adequately carried out on the basis of the thermal boundary conditions that are detected by a sensor. A thermal barrier coated component according to the present invention comprises: a base material; a first bond coat layer that is a metal bonding layer formed on the base material; a sensor unit that comprises a sensor and a conductive wire, which are formed on the first bond coat layer; a second bond coat layer that is formed on the first bond coat layer so as to cover at least the sensor unit, while having a surface roughness higher than that of the first bond coat layer; and a top coat layer that is formed on the second bond coat layer.

Thermal barrier coated component and method for producing thermal barrier coated component

A method of manufacturing a fabricated object includes forming the fabricated object by laminating metal powder, the fabricated object including an opening portion that communicates with a hollow internal space, mounting a plug in the opening portion, and welding the plug mounted in the opening portion to the fabricated object.

Method of manufacturing fabricated object

A method of forming a sprayed coating includes preparing a spray target member having a surface on which openings of first ends of holes are formed, preparing a plurality of masking pins each of which comprises metal, and inserting each of the masking pins into a corresponding one of the holes so that each of the masking pins partially protrudes from the surface. The method also includes applying an adhesive agent for fixing the masking pins to the respective holes, to at least one of the holes or the masking pins, forming a ceramic layer by spraying on the surface of the spraying target member, the ceramic layer comprising a ceramic material, while the masking pins are fixed to the respective holes via the adhesive agent, and removing the masking pins from the holes after the spraying step.

Method of forming sprayed coating, high-temperature component for turbine, turbine, masking pin for forming sprayed coating, and masking member

A unidirectionally solidified article repair method according to one embodiment includes a step of forming a groove part overlapping only on one of a plurality of crystal grain boundaries in a base material made of a unidirectionally solidified alloy in which the plurality of crystal grain boundaries are aligned in one direction, and a step of forming a welded part having a metal composition similar to that of the base material by a metal used in welding with the base material in the groove part.

Unidirectionally solidified article, turbine rotor blade and unidirectionally solidified article repair method

A method for repairing a target member including a ceramic matrix composite reinforced by ceramic fiber includes: a removal step of removing at least a part of a surface of the target member; an arrangement step of arranging a green body for repair which includes the ceramic fiber on a portion where the surface is removed in the removal step; an impregnation step of impregnating at least the portion of the target member where the green body for repair is disposed with slurry; and a sintering step of sintering the target member on which the green body for repair is disposed, after the impregnation step.

Method for repairing ceramic matrix composite and ceramic matrix composite member

A thermal barrier coating film includes a bond coat layer that is a metallic bond layer formed on a base material; a topcoat layer that is a ceramic-containing layer formed on the bond coat layer; and at least one of a protective layer and a protective substance. The protective layer is formed on the topcoat layer and mainly contains SrSO. The protective substance is provided in a plurality of void spaces included in the topcoat layer and mainly contains SrSO.

Thermal barrier coating film, turbine member, and thermal barrier coating method

A thermal barrier coating includes a highly porous layer and a dense layer. The highly porous layer is formed on a heat-resistant base, is made of ceramic, has pores, has a layer thickness of equal to or larger than 0.3 mm and equal to or smaller than 1.0 mm, and has a pore ratio of equal to or higher than 1 vol % and equal to or lower than 30 vol %. The dense layer is formed on the highly porous layer, is made of ceramic, has a pore ratio of equal to or lower than 0.9 vol % that is equal to or lower than the pore ratio of the highly porous layer, and has a layer thickness of equal to or smaller than 0.05 mm.

Thermal barrier coating, turbine member, and gas turbine

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

It is an object to provide a repairing method for a wall member with flow passages capable of reducing the time and the cost required for a partial repairing work on the wall member with flow passages. The repairing method for the wall member with flow passages includes a removal stage of removing a portion of the wall member with flow passages () provided with plural flow passages () between the base member () and the plate member (), the base member welding stage of welding the repairing base member () to the portion removed in the removal stage, a flow passage forming stage of providing plural overlay welds on the repairing base member () and forming the flow passages () between the overlay welded beads (), and a plate member welding stage of welding a repairing plate member () onto surfaces of the plural overlay welded beads ().

Repairing method for wall member with flow passages

A turbine rotor blade repair method which reduces the occurrence of cracks due to welding is provided. A turbine rotor blade repair method for repairing damage of a fin at a tip of a turbine rotor blade includes overlaying a damaged portion of the fin with metal by welding (step S); peening on a boundary region between the fin and the overlaying metal (step S); and after the peening, performing solution treatment to repair the damage of the fin of the turbine rotor blade (step S).

Turbine rotor blade repair method

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Tokyo, Japan

Masahiko Mega