Abstract: A method for producing a turbine component including: a shaping step in which, metal powder is bonded together and solidified to form an additively manufactured object having inner passages and discharge passages communicating with the inner passages; and a powder removal step in which unnecessary metal powder remaining in the inner passages is removed. The inner passages have introduction openings that are open in outer surfaces of the additively manufactured object excluding the base-facing surface, which is the outer surface facing the base plate. The discharge passages have discharge openings that are open in the plurality of outer surfaces excluding the base-facing surface. In the powder removal step, a gas is introduced through the introduction openings of the inner passages into the inner passages and the powder remaining in the inner passages is discharged through the discharge openings of the discharge passages together with the gas.

Abstract: A method of manufacturing an additively manufactured object includes: checking, for an additively manufactured object including a plurality of internal passages, the presence or absence of a deposit in each inner wall surface of the plurality of internal passages; and selectively removing the deposit from the internal passage in which the deposit has been detected in the checking, among the plurality of internal passages.

Abstract: A turbine blade includes a blade body, cooling passages extending in the blade height direction inside the blade body and connected to each other via folded portions, and a bypass portion that is provided in a partition wall portion partitioning a pair of adjacent cooling passages and that allows the pair of cooling passages to communicate with each other. The pair of cooling passages includes an upstream passage and a downstream passage. The turbine blade is provided with: a plurality of cooling holes formed in the blade body so as to be arranged along the blade height direction, that communicate with the downstream passage, and open in the surface of the blade body; a plurality of turbulators provided on the inner wall surface of the downstream passage and arranged along the blade height direction; or a thermal barrier coating that covers the surface of the blade body.

Abstract: A turbine blade includes a blade body, cooling passages extending in the blade height direction inside the blade body and connected to each other via folded portions, and a bypass portion that is provided in a partition wall portion partitioning a pair of adjacent cooling passages and that allows the pair of cooling passages to communicate with each other. The pair of cooling passages includes an upstream passage and a downstream passage. The turbine blade is provided with: a plurality of cooling holes formed in the blade body so as to be arranged along the blade height direction, that communicate with the downstream passage, and open in the surface of the blade body; a plurality of turbulators provided on the inner wall surface of the downstream passage and arranged along the blade height direction; or a thermal barrier coating that covers the surface of the blade body.

Abstract: This component inspection method includes: a fluid supply step for supplying a fluid to a cooling flow passage of a component internally including said cooling flow passage; a heating step for heating a surface of the component; and a measurement step for measuring a temperature of the surface of the component heated by means of the heating step.

Abstract: The disclosure provides a method comprising (1) conducting a PCR using a nucleic acid sample obtained from the subject as the template, a forward primer having a nucleic acid sequence of a part of exon 1 of the BCR gene, and a reverse primer having a nucleic acid sequence complementary to a part of exons 2 to 11 of the ABL1 gene, in the presence of a modified nucleic acid having a nucleic acid sequence of a part of exons 2 to 14 of the BCR gene or a nucleic acid sequence complementary thereto; and (2) determining that the subject has the minor BCR-ABL1 gene when the nucleic acid amplification is occurred in the PCR.

Abstract: A high-temperature component according to an embodiment is a high-temperature component which requires to be cooled by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; and a first partition wall disposed inside each of the cooling passages to partition the cooling passage into a plurality of first branch flow passages. The first partition wall includes an oblique portion formed such that, in an upstream side region of the first partition wall, a flow-passage cross-sectional area of the cooling passage as seen in an extension direction of the cooling passage gradually decreases from an upstream side toward a downstream side.

Abstract: A high-temperature component according to an embodiment is a high-temperature component which requires cooling by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; a header portion to which downstream ends of the plurality of first cooling passages are connected; and at least one outlet passage for discharging the cooling medium flowing into the header portion to outside of the header portion. A roughness of an inner wall surface of the at least one outlet passage is not greater than a roughness of an inner wall surface of the plurality of first cooling passages in a region where a flow-passage cross-sectional area of the outlet passage is the smallest.

Abstract: A high-temperature component including a plurality of cooling passages through which the cooling medium can flow, a header connected to respective downstream ends of the plurality of cooling passages, and one or more outlet passages for discharging the cooling medium flowing into the header to outside of the header. The one or more outlet passages are less in number than the plurality of cooling passages. Respective minimum flow passage cross-sectional areas of the one or more outlet passages are not less than respective flow passage cross-sectional areas of the plurality of cooling passages in a connection between the header and the cooling passages. A sum of the respective minimum flow passage cross-sectional areas of the one or more outlet passages is less than a sum of the respective flow passage cross-sectional areas of the plurality of cooling passages in the connection between the header and the cooling passages.

Abstract: A method of manufacturing an additively manufactured object includes: checking, for an additively manufactured object including a plurality of internal passages, the presence or absence of a deposit in each inner wall surface of the plurality of internal passages; and selectively removing the deposit from the internal passage in which the deposit has been detected in the checking, among the plurality of internal passages.

Abstract: 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.

Abstract: A high-temperature component according to an embodiment is a high-temperature component which requires to be cooled by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; and a first partition wall disposed inside each of the cooling passages to partition the cooling passage into a plurality of first branch flow passages. The first partition wall includes an oblique portion formed such that, in an upstream side region of the first partition wall, a flow-passage cross-sectional area of the cooling passage as seen in an extension direction of the cooling passage gradually decreases from an upstream side toward a downstream side.

Abstract: A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up<d_mid<d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.

Abstract: A high-temperature component according to an embodiment is a high-temperature component which requires cooling by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; a header portion to which downstream ends of the plurality of first cooling passages are connected; and at least one outlet passage for discharging the cooling medium flowing into the header portion to outside of the header portion. A roughness of an inner wall surface of the at least one outlet passage is not greater than a roughness of an inner wall surface of the plurality of first cooling passages in a region where a flow-passage cross-sectional area of the outlet passage is the smallest.

Abstract: A high-temperature component including a plurality of cooling passages through which the cooling medium can flow, a header connected to respective downstream ends of the plurality of cooling passages, and one or more outlet passages for discharging the cooling medium flowing into the header to outside of the header. The one or more outlet passages are less in number than the plurality of cooling passages. Respective minimum flow passage cross-sectional areas of the one or more outlet passages are not less than respective flow passage cross-sectional areas of the plurality of cooling passages in a connection between the header and the cooling passages. A sum of the respective minimum flow passage cross-sectional areas of the one or more outlet passages is less than a sum of the respective flow passage cross-sectional areas of the plurality of cooling passages in the connection between the header and the cooling passages.

Abstract: A turbine blade includes a blade body including a top plate at a tip portion which is outside of a turbine rotor in a radial direction of the turbine blade and has an outer surface configured to face an inner circumferential surface of a casing, and a tip thinning which protrudes radially outward in the radial direction of the turbine blade from the outer surface of the top plate and extends from a leading edge side of the blade body to a trailing edge side of the blade body. A protrusion amount of the tip thinning based on the outer surface of the top plate is 0.25 times or more and 2.00 times or less a diameter of a discharge port of a cooling hole which passes through the top plate.

Abstract: A second outer surface (49ab) of a top plate (49) is recessed from a first outer surface (49aa) of the top plate (49) in the direction away from the inner peripheral surface (34a) of a turbine casing (34) so that a step (50) is formed between the second outer surface (49ab) and the first outer surface (49aa). At least part of the discharge opening (53B) of a cooling hole (53) is disposed in the second outer surface (49ab). The cooling hole (53) extends so as to be tilted relative to the second outer surface (49ab) so that the cooling hole (53) discharges a cooling medium to the upstream side of a combustion gas flowing between the second outer surface (49ab) and the inner peripheral surface (34a) of the turbine casing (34).

Abstract: 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.

Abstract: A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up<d_mid<d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.

Abstract: A second outer surface (49ab) of a top plate (49) is recessed from a first outer surface (49aa) of the top plate (49) in the direction away from the inner peripheral surface (34a) of a turbine casing (34) so that a step (50) is formed between the second outer surface (49ab) and the first outer surface (49aa). At least part of the discharge opening (53B) of a cooling hole (53) is disposed in the second outer surface (49ab). The cooling hole (53) extends so as to be tilted relative to the second outer surface (49ab) so that the cooling hole (53) discharges a cooling medium to the upstream side of a combustion gas flowing between the second outer surface (49ab) and the inner peripheral surface (34a) of the turbine casing (34).