摘要:
A high temperature corrosion resistant alloy composition comprising, in addition to Ni, 0.1 to 12% by weight of Co, 10 to 30% by weight of Cr, 4 to 15% by weight of Al, 0.1 to 5% by weight of Y, and 0.5 to 10% by weight of Re. The high temperature corrosion resistant alloy composition has an excellent oxidation resistance and ductility and is suitable for use in a bonding layer of a thermal barrier coating material.
摘要:
In a specimen collecting method according to the present invention, a specimen is collected from a surface (114a) of a blade. An ultrasonic cutter having a cylindrical cutting blade is fed from the surface (114a) of the blade to a surface (110a) of a base material (100), and thus, a cylindrical incision is formed. After performing cutting to expand the incision outwardly, a rotating cutter (220) having a disc-shaped cutting blade (222) performs cutting inwardly from the cylindrical incision. Thus, a part (20a) situated inside the incision is cut away. The part (20a) becomes the specimen.
摘要:
In a specimen collecting method according to the present invention, a specimen is collected from a surface (114a) of a blade. An ultrasonic cutter having a cylindrical cutting blade is fed from the surface (114a) of the blade to a surface (110a) of a base material (100), and thus, a cylindrical incision is formed. After performing cutting to expand the incision outwardly, a rotating cutter (220) having a disc-shaped cutting blade (222) performs cutting inwardly from the cylindrical incision. Thus, a part (20a) situated inside the incision is cut away. The part (20a) becomes the specimen.
摘要:
An alloy material having high-temperature corrosion resistance, which exhibits excellent oxidation resistance and ductility and can be applied to gas turbines used at ultra high temperatures, and a thermal barrier coating, a turbine member and a gas turbine each comprising the alloy material. An alloy material having high-temperature corrosion resistance, comprising, by weight, Co: 15 to 30%, Cr: 10 to 30%, Al: 4 to 15%, Y: 0.1 to 3%, and Re: 0.1 to 1%, with the balance being substantially Ni. Also, an alloy material having high-temperature corrosion resistance, comprising, by weight, Ni: 20 to 40%, Cr: 10 to 30%, Al: 4 to 15%, Y: 0.1 to 3%, and Re: 0.1 to 5%, with the balance being substantially Co.
摘要:
The present invention provides an oxidation-resistant coating having superior oxidation resistance and superior ductility and toughness for long-term use, and a method for forming the oxidation-resistant coating. An MCrAlY layer primarily containing an MCrAlY alloy (in which M indicates at least one element of Co and Ni) is formed on a substrate formed of a heat-resistant metal by thermal spraying or EB=PVD, and subsequently, aluminum is diffused into a part of the MCrAlY layer in the thickness direction thereof from a side opposite to the substrate.
摘要:
An alloy material having high-temperature corrosion resistance, which exhibits excellent oxidation resistance and ductility and can be applied to gas turbines used at ultra high temperatures, and a thermal barrier coating, a turbine member and a gas turbine each comprising the alloy material. An alloy material having high-temperature corrosion resistance, comprising, by weight, Co: 15 to 30%, Cr: 10 to 30%, Al: 4 to 15%, Y: 0.1 to 3%, and Re: 0.1 to 1%, with the balance being substantially Ni. Also, an alloy material having high-temperature corrosion resistance, comprising, by weight, Ni: 20 to 40%, Cr: 10 to 30%, Al: 4 to 15%, Y: 0.1 to 3%, and Re: 0.1 to 5%, with the balance being substantially Co.
摘要:
A thermal barrier coating material can prevent spall-off from occurring during operation at high temperatures and has a high heat insulating effect. A turbine parts and a gas turbine that are protected with the thermal barrier coating material are also provided. The thermal barrier coating material of the present invention comprises a ceramic layer 23, which is formed on a high temperature heat-resistant alloy base 21 to protect the base 21 from high temperatures, the ceramic layer 23 being applied via a bonding coat layer 22 provided as a metal bonding layer and is made of ZrO2 with Er2O3 added thereto as a stabilizing agent. The turbine parts and the gas turbine of the present invention are coated with the thermal barrier coating material on the surfaces thereof.
摘要翻译:热障涂层材料可以防止在高温运行时发生剥落,并且具有高隔热效果。 还提供了用热障涂层材料保护的涡轮部件和燃气轮机。 本发明的隔热涂料包括陶瓷层23,该陶瓷层23形成在高温耐热合金基体21上,以保护基底21免受高温的影响,陶瓷层23通过提供的接合涂层22施加 作为金属结合层,并且由添加有Er 2 O 3 N 3的ZrO 2 2作为稳定剂制成。 本发明的涡轮机部件和燃气轮机在其表面上涂覆有热障涂层材料。
摘要:
A thermal barrier coating material, containing a metal binding layer laminated on a base material and ceramic layer laminated on the metal binding layer, the ceramic layer comprising partially stabilized ZrO2 which is partially stabilized by additives of Dy2O3 and Yb2O3.
摘要:
A thermal barrier coating material, containing a metal binding layer laminated on a base material and a ceramic layer laminated on the metal binding layer, the ceramic layer comprising partially stabilized ZrO2 which is partially stabilized by additives of Dy2O3 and Yb2O3.
摘要:
The present invention relates to a method of repairing a Ni-based alloy part having an undercoat layer and a topcoat layer stacked on a Ni-based alloy base when the topcoat layer is damaged, comprising the steps of removing a peeled-off portion of the damaged topcoat layer and a denatured portion of the undercoat layer corresponding to the peeled-off portion, forming another undercoat layer by applying spraying to an opening portion of the undercoat layer in the atmosphere at a spray particle speed of 300 m/s or more and a base-material temperature of 300° C. or less, and forming another topcoat layer in the peeled-off portion of the topcoat layer