Mitsubishi Heavy Industries Limited

Tsinghua University

Mitsubishi Hitachi Power Systems, Ltd.

Katsumi Namba

Kazutaka Mori

Ikuo Okada

Taiji Torigoe

Koji Takahashi

Ichiro Nagano

Masahiro Yamada

Eisaku Ito

Ichiro Ichihashi

Yasuhiko Tsuru

Yutaka Kawata

Qiang Xu

Masato Shida

Wei Pan

Yosuke Kawachi

Motoyoshi Nakamura

Yasuki Date

Rin Okayasu

Ryosuke Kimura

Masaharu Ishida

Tomohiro Ono

A repair method for a gas turbine blade. The repair method include: a step of removing a thermal barrier coating to expose at least part of a base material of the gas turbine blade; a first etching step of etching the exposed base material; and a first identification step of identifying a base material deterioration layer that is harder than the base material from the etched base material. The repair method further includes a first removal step of removing the identified base material deterioration layer if the base material deterioration layer is identified in the first identification step; and a step of applying a thermal barrier coating to the exposed base material. The thermal barrier applying step is performed after it is determined that there is no base material deterioration layer in the first identification step, or after the base material deterioration layer is removed in the first removal step.

Gas turbine blade repair method

There are provided a thermal barrier coating material and a thermal barrier coating member that can suppress spalling when used at a high temperature and have a high thermal barrier effect, a method for producing the same, a turbine member coated with a thermal barrier coating, and a gas turbine. The thermal barrier coating member comprises a heat resistant substrate, a bond coat layer formed thereon, and a ceramic layer formed further thereon, wherein the ceramic layer comprises an oxide which consists of an oxide represented by the general formula AZrOdoped with a predetermined amount of CaO or MgO and has 10 volume % or more of a pyrochlore type crystal structure, where A represents any of La, Nd, Sm, Gd, and Dy.

Thermal barrier coating member, method for producing the same, thermal barrier coating material, gas turbine, and sintered body

A method by which physical properties, including the Young's modulus and thermal conductivity of a ceramic layer of a thermal barrier coating formed on a high-temperature member, are quickly and accurately estimated. A method for estimating a physical property of a ceramic includes a step of calculating the Larson-Miller parameter from the time for which and the temperature at which the ceramic is heated; a step of acquiring the porosity of the ceramic corresponding to the calculated Larson-Miller parameter, based on the calculated Larson-Miller parameter and a diagram correlating the Larson-Miller parameter and the porosity obtained from samples having the same composition as the ceramic; and a step of acquiring the physical property of the ceramic corresponding to the acquired porosity, based on the acquired porosity and a diagram correlating the porosity and the physical property obtained from samples having the same composition as the ceramic.

Method for estimating physical property of ceramic, method for estimating physical property of thermal barrier coating, method for estimating remaining lifetime of thermal barrier coating, method for estimating remaining lifetime of high-temperature member, and physical property acquiring apparatus

Provided are a thermal barrier coating material and a member coated with thermal barrier that can suppress the separation when used at a high temperature, and have a high thermal barrier effect; a method for manufacturing the member coated with thermal barrier; a turbine member coated with the thermal barrier coating material; and a gas turbine. More specifically provided are a shield coating member comprising a heat-resistant substrate, a bond coat layer formed on the heat-resistant substrate, and a ceramic layer formed on the bond coat layer, wherein the ceramic layer comprises a ceramic represented by a general formula AZrO, wherein A denotes a rare earth element, and the ceramic layer has (a) a porosity of 1 to 30%, (b) cracks in a thickness direction in pitches of 5 to 100% the total thickness of layers other than the bond coat layer on the heat-resistant substrate, or (c) columnar crystals.

Thermal barrier coating material, thermal barrier member, and member coated with thermal barrier and method for manufacturing the same

Growing community of inventors

Takasago, Japan

Katsumi Namba