Abstract: The present invention provides a corrosion loss measuring apparatus which enables to quantitatively determine corrosion loss characteristics of ceramic materials and heat-resistant metallic materials, which is excellent in terms of safety, cost, and operation easiness, and whose size can be reduced. The invention also provides a method for measuring corrosion loss by use of the apparatus.

Abstract: There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat is formed of a ceramic on a bond coat, the bond coat being formed on a heat resistant alloy substrate composed mainly of at least one element of nickel and cobalt, wherein the bond coat contains at least one of nickel and cobalt, chromium and aluminum, and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt %. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.

Abstract: A corrosion-resistant silicon nitride ceramics in which an adhesion enhancing layer (3), a stress relaxing layer (4) and a crack extension preventing layer (5) are laminated in this order on a ceramic substrate (2) composed mainly of silicon nitride, and a surface corrosion-resistant layer (6) composed mainly of zirconium oxide stabilized by an element of the group 3a of the periodic table is laminated. The thermal expansion coefficient (?0) of the ceramic substrate (2), the thermal expansion coefficient(?1) of the adhesion enhancing layer (3), and the thermal expansion coefficient (?2) of the stress relaxing layer (4), the thermal expansion coefficient (?3) of the crack extension preventing layer (5), and the thermal expansion coefficient (?4) of the surface corrosion-resistant layer (6) satisfy the following relational expressions (I) to (III): ?0??1??(I) ?3<?2??(II) ?3<?4??(III).

Abstract: There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat is formed of a ceramic on a bond coat, the bond coat being formed on a heat resistant alloy substrate composed mainly of at least one element of nickel and cobalt, wherein the bond coat contains at least one of nickel and cobalt, chromium and aluminum, and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt %. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.

Abstract: A corrosion-resistant silicon nitride ceramics in which an adhesion enhancing layer (3), a stress relaxing layer (4) and a crack extension preventing layer (5) are laminated in this order on a ceramic substrate (2) composed mainly of silicon nitride, and a surface corrosion-resistant layer (6) composed mainly of zirconium oxide stabilized by an element of the group 3a of the periodic table is laminated.

Abstract: The present invention provides a corrosion loss measuring apparatus which enables to quantitatively determine corrosion loss characteristics of ceramic materials and heat-resistant metallic materials, which is excellent in terms of safety, cost, and operation easiness, and whose size can be reduced. The invention also provides a method for measuring corrosion loss by use of the apparatus.

Abstract: Anti-corrosion ceramics comprising a substrate of at least one kind of silicon-containing ceramics selected from a silicon nitride, a silicon carbide and Sialon, and a surface protection layer formed on the surface of the substrate, wherein the surface protection layer comprises a zirconium oxide stabilized with an element of the Group IIIa of periodic table, and the total amount of Al and Si in the surface protection layer is suppressed to be not larger than 1% by mass. Particularly, the surface layer has a thickness of from 5 to 200 &mgr;m and a porosity of 5 to 30%. The anti-corrosion ceramics exhibits a high resistance against the corrosion due to the water vapor of high temperatures in a region of not lower than 1000° C., and can be preferably used as parts of internal combustion engines such as parts of gas turbine engines, like a turbine rotor, nozzles, a combustor liner and a transition duct.

Abstract: Anti-corrosion ceramics comprising a substrate of at least one kind of silicon-containing ceramics selected from a silicon nitride, a silicon carbide and Sialon, and a surface protection layer formed on the surface of the substrate, wherein the surface protection layer comprises a zirconium oxide stabilized with an element of the Group IIIa of periodic table, and the total amount of Al and Si in the surface protection layer is suppressed to be not larger than 1% by mass. Particularly, the surface layer has a thickness of from 5 to 200 &mgr;m and a porosity of 5 to 30%. The anti-corrosion ceramics exhibits a high resistance against the corrosion due to the water vapor of high temperatures in a region of not lower than 1000° C., and can be preferably used as parts of internal combustion engines such as parts of gas turbine engines, like a turbine rotor, nozzles, a combustor liner and a transition duct.