Abstract: Ceramic thermal spray particles according to the present invention contain ZrO2 and Yb2O3, wherein the standard deviation of the content of the Yb2O3 is 2-7.0 mass %.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud.

Abstract: A method for applying a thermal barrier coating according to at least one embodiment of the present disclosure includes: a step of forming a bond coat layer by high velocity flame spraying on a heat-resistant alloy base material of an object disposed in a thermal spray booth, with a thermal spray gun disposed in the thermal spray booth; and a step of forming a top coat layer by thermal-spraying a suspension containing ceramic powder by high velocity flame spraying on the bond coat layer of the object disposed in the thermal spray booth, with the thermal spray gun disposed in the thermal spray booth.

Abstract: A method for applying a thermal barrier coating according to at least one embodiment of the present disclosure includes: a step of forming a top coat layer on a bond coat layer formed on a heat-resistant alloy base material of an object. The step of forming the top coat layer includes forming the top coat layer by thermal-spraying a suspension containing ceramic powder by high velocity flame spraying, while maintaining a temperature of the top coat layer at not lower than 300° C. and not higher than 450° C.

Abstract: A method for applying a thermal barrier coating according to at least one embodiment of the present disclosure includes: a step of forming a top coat layer on a bond coat layer, which is formed on a heat-resistant alloy base material, by thermal spraying, while ejecting a gas from a plurality of holes opened in a surface of the heat-resistant alloy base material.

Abstract: A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud.

Abstract: The present disclosure provides an analyzer with a reduced adverse effect to photometry accompanying acceleration or deceleration of a cuvette table. An actuator drives a cuvette table where a plurality of cuvettes are disposed annularly so that the cuvette table performs intermittent rotation in which a resting state and a rotating state are repeatedly alternated, and each time the cuvette table rotates intermittently, a row of the plurality of cuvettes is displaced in the annular direction by a given number of cuvettes. In the resting state, a pretreatment part performs pretreatment to a cuvette that stands still at a pretreatment position, and a post treatment part performs post treatment to a cuvette that stands still at a post treatment position. In the rotating state, a photometry part performs photometry to a cuvette that passes through a photometric position.

Abstract: 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.

Abstract: A testing method of thermal barrier coating (TBC) is for evaluating the presence or absence of damage to TBC formed on a bending part on which compression stress acts. The method includes a test piece that includes a pair of arm parts, a bending part arranged between the pair of arm parts, and a TBC layer on a bending surface of the bending part; attaching the test piece to a compression testing device after preparing the test piece; and applying compression stress to the test piece in a direction for bringing the pair of arm parts close together after attaching the test piece with the compression testing device. The pair of arm parts are arranged so as to separate from each other from base end portions toward front end portions of the arm parts. The bending part is arranged between the base end portions.

Abstract: 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.

Abstract: A turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade are disclosed. The turbine blade has a blade body having hollow shape, cavities defined inside the blade body, and a cooling passage that opens from the cavities to a rear end portion of the blade body. The cooling passage includes: a first passage on a third cavity side and having a width that becomes narrower from the third cavity side toward the rear end portion of the blade body; and a second passage on a rear end portion side of the blade body and having a width that is constant from the third cavity side toward the rear end portion of the blade body.

Abstract: An object of the present invention is to provide a turbine rotor blade or the like capable of improving the durability of a contact surface and the reliability of the blade. The turbine rotor blade includes a blade body and a tip shroud that is provided to a tip of the blade body. The tip shroud has a contact block facing an adjacent tip shroud, and the contact block includes a base material, an oxidation resistant coating laid on the surface of the base material, and a hard wear resistant coating that is laid on the surface of the oxidation resistant coating.

Abstract: 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.

Abstract: The task is to provide a thermal barrier coating film (13) which exhibits high durability even in a gas turbine that is used under a molten salt environment, such as a heavy oil fired gas turbine, and which can be efficiently formed at low cost without requiring complicated processes, and a thermal barrier coating film (13) configures a turbine member includes a ceramic material thermally sprayed and formed on a base material (10) made of a heat resistant alloy, in which ytterbia partially stabilized zirconia is used as the ceramic material of the film (13), and the porosity of the film (13) is 5% or more and less than 8%.

Abstract: 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 SrSO4. The protective substance is provided in a plurality of void spaces included in the topcoat layer and mainly contains SrSO4.

Abstract: 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.