Mitsubishi Heavy Industries Aero Engines, Ltd.

Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Takayuki Kurimura

Mineaki Matsumoto

Tadayuki Hanada

Kosuke Nishikawa

Azusa Tamugi

Yoshifumi Tsuji

Hidekazu Uehara

Taiji Torigoe

Soichiro Tabata

Masahiko Mega

Shuji Tanigawa

Naoto Tochitani

Ryuta Ito

Yuichi Hirakawa

Naotoshi Okaya

Yuki Enomoto

Shunji Imai

Yamato Shiramasa

Yuta Okimori

Haruhiko Asaka

Tanehiro Sinohara

Takasi Nakano

Sin Nisimoto

Tatsuji Takahasi

Sin Koga

Provided are a coated member in which damage of a coating film can be suppressed in a high temperature environment and the coating may be performed at low cost, and a method of manufacturing the same. A coated member includes a bond coat and a top coat sequentially laminated on a substrate made of a Si-based ceramic or a SiC fiber-reinforced SiC matrix composite, wherein the top coat includes a layer composed of a mixed phase of a (YLn)SiOsolid solution (here, Lnis any one of Nd, Sm, Eu, and Gd) and YSiOor a (YLn')SiOsolid solution (here, Ln&#x2032; is any one of Nd, Sm, Eu, and Gd), or a mixed phase of a (YLn)SiOsolid solution (here, Lnis any one of Sc, Yb, and Lu) and YSiOor a (YLn&#x2032;)SiOsolid solution (here, Ln&#x2032; is any one of Sc, Yb, and Lu).

Coated member and method of manufacturing the same

A coating method includes depositing a slurry including a coarsely particulate ceramic and a finely particulate ceramic on a base material configured with an oxide-based ceramics matrix composite such that a proportion of coarse particles decreases towards a surface of the base material; forming a bond coating by performing a heat treatment on the base material on which the slurry has been deposited; and forming a top coating by thermally spraying a ceramic onto the bond coating. The oxide-based ceramics matrix composite is an alumina silica type oxide-based ceramics matrix composite. The coarsely particulate ceramic and the finely particulate ceramic are alumina-based powder.

Coating method, coating layer, and turbine shroud

A ring-segment surface-side member is included in a ring segment disposed at a position opposite to a turbine blade on a stationary side of a gas turbine, serves as a part of a combustion gas flow path through which combustion gas flows, and is formed of a ceramic matrix composite. The ring-segment surface-side member includes: a surface portion forming the combustion gas flow path; a turned-back portion including a first part extending outward in a radial direction of the gas turbine from the surface portion and a second part extending toward a central line of the surface portion from an end part of the first part; and a protrusion portion extending outward from the turned-back portion in the radial direction of the gas turbine.

Ring-segment surface-side member, ring-segment support-side member, ring segment, stationary-side member unit, and method

Provided are a coating structure, a turbine part having the same, and a method for manufacturing the coating structure. The coating structure is provided on a surface of a base portion including a ceramic matrix composite. The coating structure is layered on the surface of the base portion, and includes a bond coat layer formed of a rare-earth silicate and a top coat layer layered on the bond coat layer. The residual stress present in the bond coat layer is compressive residual stress. The oxygen permeability coefficient of the bond coat layer is no greater than 10kg&#xb7;m&#xb7;sat a temperature of not lower than 1200&#xb0; C. and a higher oxygen partial pressure of not less than 0.02 MPa. The bond coat layer may contain carbonitride particles or carbonitride whiskers.

Coating structure, turbine part having same, and method for manufacturing coating structure

Provided are a coated member in which damage of a coating film can be suppressed in a high temperature environment and the coating may be performed at low cost, and a method of manufacturing the same. A coated member includes a bond coat and a top coat sequentially laminated on a substrate made of a Si-based ceramic or a SiC fiber-reinforced SiC matrix composite, wherein the top coat includes a layer composed of a mixed phase of a (YLn)SiOsolid solution (here, Lnis any one of Nd, Sm, Eu, and Gd) and YSiOor a (YLn)SiOsolid solution (here, Lnis any one of Nd, Sm, Eu, and Gd), or a mixed phase of a (YLn)SiOsolid solution (here, Lnis any one of Sc, Yb, and Lu) and YSiOor a (YLn)SiOsolid solution (here, Lnis any one of Sc, Yb, and Lu).

A coated member includes a heat-shielding coating layer made of a zirconia-dispersed silicate in which ytterbia-stabilized zirconia is precipitated as a dispersed phase in a matrix phase which is any one of a rare earth disilicate, a rare earth monosilicate, and a mixed phase of the rare earth disilicate and the rare earth monosilicate. The rare earth disilicate is a (Y[Ln])SiOsolid solution wherein Lnis any one of Sc, Yb, and Lu, or a (Y[Ln])SiOsolid solution wherein Lnis any one of Nd, Sm, Eu, and Gd. The rare earth monosilicate is YSiO, [Ln']SiO, a (Y[Ln&#x2032;]b)SiOsolid solution wherein Ln&#x2032; is any one of Sc, Yb, and Lu, or a (Y[Ln&#x2032;])SiOsolid solution wherein Ln&#x2032; is any one of Nd, Sm, Eu, and Gd.

Coated member, coating material, and method of manufacturing coated member

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 method for constructing an abradable coating comprises: a slurry layer formation step Sin which a slurry layeris formed on the surface of a base materialusing a slurry containing ceramic particles and a solvent; a calcination step Sin which the slurry layerformed on the surface of the base materialis sintered and a sintered layerto be a portion of an abradable coating layeris formed; and a slurry removal step Sin which extraneous slurry is removed after the abradable coating layerhas been formed on the surface of the base material, a plurality of the sintered layershaving been laminated in the abradable coating layerthrough a plurality of repeated cycles of the slurry layer formation step Sand the calcination step S

Method for constructing abradable coating, and shroud

A steam turbine rotor blade for forming a turbine rotor cascade of a steam turbine includes a rotor blade main body having a blade portion, a blade base portion and a first coupling portion, which has first facing surfaces, provided on opposite end sides of the blade portion, and a second coupling portion provided in an intermediate portion of the blade portion and having second facing surfaces. The steam turbine rotor blade also includes a coating layer which is made of a Co-based alloy having a single composition on a surface of at least one of the first and second facing surfaces with a diffusion layer having a thickness of 10 &#x3bc;m or less provided between the coating layer and the surface.

Steam turbine rotor blade, method for manufacturing steam turbine rotor blade, and steam turbine

A method for implementing an abradable coating comprising: a pattern-forming step in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a firing step in which the slurry pattern formed on the surface of the thermal barrier coating layer is fired to form an abradable coating layer. A ceramic material included in the thermal barrier coating layer and ceramic particles included in the abradable coating layer are of the same type.

Shroud and method for implementing abradable coating

In a method of manufacturing an axis seal, first, a roll of rolled metal material is cut into metal material plates of a predetermined size. Next, metal material plates are etched from both sides so as to form a predetermined size. Subsequently, the thin metal plates are arranged so as to be in a ring shape, oriented in the same direction, and are welded so as to be fixed. Additionally, during these processes, heat treatment is performed by heating rolls of rolled metal materials or metal material plates or thin metal plates at a predetermined timing, thereby eliminating residual stress (strain).

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Tokyo, Japan

Takayuki Kurimura