Abstract: A turbine stator vane includes: a vane body which includes: an airfoil portion which has a serpentine flow passage inside thereof, the serpentine flow passage including a plurality of cooling flow passages and a plurality of turn-back flow passages; a shroud disposed on at least one of a tip end side or a root end side, in the vane height direction, of the airfoil portion; and a lid portion fixed to the airfoil portion. The lid portion forming the turn-back flow passage and being provided as a separate member from the airfoil portion. The lid portion has an inner wall surface width formed to be greater than the flow-passage width of the cooling passage formed in the airfoil portion, and a minimum value of a thickness of the lid portion is smaller than a thickness of a part of the shroud to which the lid portion is mounted.

Abstract: A stator vane includes a blade body, an outer shroud, and an impingement plate. The outer shroud includes a recess. The impingement plate forms a cavity inside the recess. A communication hole is provided in the impingement plate and the outer shroud. In the impingement plate, a plurality of through holes through which an outer space and a cavity communicate with each other are formed. A second region in which an opening ratio is large and a first region in which an opening ratio is small exist in a surface of the impingement plate.

Abstract: A turbine blade includes an airfoil portion having a hollow portion extending along the blade height direction and film cooling holes arranged along the blade height direction, and an insert disposed in the hollow portion along the blade height direction and having impingement cooling holes. The insert includes a first high-density opening region having a higher density of the impingement cooling holes than in other surface regions of the insert. The geometric center of the first high-density opening region is positioned on the suction side of the airfoil portion in the leading-edge-to-trailing-edge direction and on the outer side of the midpoint of the airfoil portion in the blade height direction. The film cooling holes includes upstream film cooling holes disposed in the suction surface of the airfoil portion at a position corresponding to the first high-density opening region or at a position closer to a leading edge than the position.

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: A turbine stator vane includes: a vane body which includes: an airfoil portion which has a serpentine flow passage inside thereof, the serpentine flow passage including a plurality of cooling flow passages and a plurality of turn-back flow passages; a shroud disposed on at least one of a tip end side or a root end side, in the vane height direction, of the airfoil portion; and a lid portion fixed to the airfoil portion. The lid portion forming the turn-back flow passage and being provided as a separate member from the airfoil portion. The lid portion has an inner wall surface width formed to be greater than the flow-passage width of the cooling passage formed in the airfoil portion, and a minimum value of a thickness of the lid portion is smaller than a thickness of a part of the shroud to which the lid portion is mounted.

Abstract: A stator vane includes a blade body, an outer shroud, and an impingement plate. The outer shroud includes a recess. The impingement plate forms a cavity inside the recess. A communication hole is provided in the impingement plate and the outer shroud. In the impingement plate, a plurality of through holes through which an outer space and a cavity communicate with each other are formed. A second region in which an opening ratio is large and a first region in which an opening ratio is small exist in a surface of the impingement plate.

Abstract: A turbine blade includes an airfoil portion having a hollow portion extending along the blade height direction and film cooling holes arranged along the blade height direction, and an insert disposed in the hollow portion along the blade height direction and having impingement cooling holes. The insert includes a first high-density opening region having a higher density of the impingement cooling holes than in other surface regions of the insert. The geometric center of the first high-density opening region is positioned on the suction side of the airfoil portion in the leading-edge-to-trailing-edge direction and on the outer side of the midpoint of the airfoil portion in the blade height direction. The film cooling holes includes upstream film cooling holes disposed in the suction surface of the airfoil portion at a position corresponding to the first high-density opening region or at a position closer to a leading edge than the position.

Abstract: Provided are a turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade. This turbine blade has a blade body having hollow shape, cavities provided inside the blade body, and a cooling passage that opens from the cavities to the rear end portion of the blade body. The cooling passage includes: a first passage provided on the 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 provided on the 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: A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.

Abstract: The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass, Co: 8 to 12%, Cr: 5 to 7.5%, Mo: 0.2 to 1.2%, W: 5 to 7%, Al: 5 to 6.5%, Ta: 8 to 12%. Hf: 0.01 to 0.2%, Re: 2 to 4%, Si: 0.005 to 0.1%, with the balance of Ni and inevitable impurities.

Abstract: A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.

Abstract: A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.

Abstract: In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the main body of the segment body; a first cavity that receives the cooling air from the cooling space; and a first cooling passage, of which one end communicates with the first cavity, and the other end blows out the cooling air from openings that are arranged in the side end portion into combustion gas; the openings of the first cooling passages being arranged so that the arrangement pitch of the openings becomes smaller or the opening area of the openings becomes larger on the upstream in the flow direction of the combustion gas than the openings on the downstream, and are arranged so that the arrangement pitch of the openings becomes larger or the opening area of the openings becomes smaller on the downstream in the flow direction of the combust

Abstract: A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region and a second region having a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages.

Abstract: The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass, Co: 8 to 12%, Cr: 5 to 7.5%, Mo: 0.2 to 1.2%, W: 5 to 7%, Al: 5 to 6.5%, Ta: 8 to 12%. Hf: 0.01 to 0.2%, Re: 2 to 4%, Si: 0.005 to 0.1%, with the balance of Ni and inevitable impurities.

Abstract: In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the main body of the segment body; a first cavity that receives the cooling air from the cooling space; and a first cooling passage, of which one end communicates with the first cavity, and the other end blows out the cooling air from openings that are arranged in the side end portion into combustion gas; the openings of the first cooling passages being arranged so that the arrangement pitch of the openings becomes smaller or the opening area of the openings becomes larger on the upstream in the flow direction of the combustion gas than the openings on the downstream, and are arranged so that the arrangement pitch of the openings becomes larger or the opening area of the openings becomes smaller on the downstream in the flow direction of the combust

Abstract: A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes.

Abstract: A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.