Abstract: A stator vane assembly of a gas turbine includes: a stationary member formed to have an annular shape; and a plurality of stator vane segments each including a shroud and a vane body, the plurality of stator vane segments disposed along a circumferential direction of the stationary member at a radially inner side of the stationary member such that a cavity is disposed between the shrouds and the stationary member and the shrouds are disposed adjacent to one another in the circumferential direction of the stationary member. The stationary member has a hole which penetrates through the stationary member from a radially outer side toward the radially inner side, and a center axis of the hole is oriented toward a circumferential-direction end portion of the shroud.

Abstract: To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.

Abstract: This gas turbine blade comprises a platform part having a cooling passage formed inside, and a wing body part protruding from the upper surface of the platform part. A plurality of first ejection ports that eject a gas supplied from the cooling passage are formed in an inner chordal region of the upper surface, which is positioned further toward the wing-body side than a wing chord connecting the leading edge and the trailing edge of the wing body part. A plurality of second ejection ports that eject the gas supplied from the cooling passage are formed in an outer chordal region of the upper surface, which is positioned on the side opposite the inner chordal region with respect to the wing chord. The outer chordal region has an outer chordal leading edge region positioned on the leading-edge side and an outer chordal trailing edge region positioned on the trailing-edge side, more second ejection ports being formed in the outer chordal leading edge region than in the outer chordal trailing edge region.

Abstract: An antibacterial molded article that can further increase antibacterial performance. The present invention for achieving the above object is related to an antibacterial molded article including a resin molded article. The resin molded article has an antibacterial area on a surface of the resin molded article, the antibacterial area having a prominent protrusion ratio of 3% or greater and 25% or less. Alternatively, the resin molded article has an antibacterial area on a surface of the resin molded article, the antibacterial area having: a maximum height of profile defined by JIS B 0601 (2013) of 100 nm or greater and less than 500 nm, and a plurality of capture protrusions having a height of not less than half the maximum height of profile (Rz), in which an average distance between the plurality of capture protrusions is 1.5 ?m or greater and 7 ?m or less.

Abstract: To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.

Abstract: An axial-direction passage, a forced vortex passage, a first blade array passage, and a second blade array passage are formed in a rotor shaft of a turbine. Cooling air from an air extraction port of a compressor flows through the axial-direction passage which extends in an axial direction. The forced vortex passage is connected to the axial-direction passage and extends outwards in the radial direction relative to an axial line from a connecting portion between the forced vortex passage and the axial-direction passage. The first blade array passage is connected to an end portion on the outer side in the radial direction of the forced vortex passage and guides cooling air to a first blade row among a plurality of blade rows. The second blade array passage is connected to an end portion of the forced vortex passage and guides cooling air to a second blade row.

Abstract: A ring segment includes segment bodies arranged along a circumferential direction; a main cavity; first cooling channels inside the segment body to extend along an axial direction of a rotor and arrayed in the circumferential direction, and whose ends communicate with the main cavity on an upstream side thereof; a second cooling channel inside the segment body on an upstream side in a rotation direction of the rotor to extend along the axial direction, and whose first end communicates with the main cavity on the upstream side thereof; and third cooling channels to extend along the circumferential direction, in a predetermined region forming a part of a lateral end of the segment body on the upstream side and stretching from an end of the segment body on a downstream side in the combustion gas flow direction toward the upstream side, and whose first ends communicate with the second cooling channel.

Abstract: A turbine blade includes: an airfoil body; a cooling passage extending along a blade height direction inside the airfoil body; and a plurality of turbulators disposed on an inner wall surface of the cooling passage and arranged along the cooling passage. The airfoil body has a first end portion and a second end portion which are opposite end portions in the blade height direction. A passage width of the cooling passage in a suction-pressure direction of the airfoil body at the second end portion is greater than a passage width of the cooling passage at the first end portion. A height of the plurality of turbulators increases from a first end portion side to a second end portion side in the blade height direction.

Abstract: A turbine blade includes a blade body in which a suction side (51) facing one side in a circumferential direction and a pressure side (52) facing the other side in the circumferential direction are connected at a leading edge and a trailing edge; and a shroud provided at a tip which is a radially outer end portion of the blade body. The shroud includes a shroud body having an outer circumferential surface facing radially outward, a front end surface extending to both sides in the circumferential direction with a leading edge side of the blade body as a reference point (P1), a rear end surface extending to both sides in the circumferential direction with a trailing edge side of the blade body as a reference point (P2), and a contact surface provided on both sides in the circumferential direction, and a reinforcing portion which protrudes from the outer circumferential surface.

Abstract: A turbine blade includes: an airfoil body; a cooling passage extending along a blade height direction inside the airfoil body; and a plurality of turbulators disposed on an inner wall surface of the cooling passage and arranged along the cooling passage. The airfoil body has a first end portion and a second end portion which are opposite end portions in the blade height direction. A passage width of the cooling passage in a suction-pressure direction of the airfoil body at the second end portion is greater than a passage width of the cooling passage at the first end portion. A height of the plurality of turbulators increases from a first end portion side to a second end portion side in the blade height direction.

Abstract: A turbine blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a leading edge-side cooling passage (64), a trailing edge-side cooling passage (67), and a middle cooling passage (65). The tip shroud (52) is provided with a first discharge passage (72), a second discharge passage (73), and a third discharge passage (74). The first discharge passage (72) discharges a cooling medium flowing through the leading edge-side cooling passage (64). The second discharge passage (73) discharges a cooling medium flowing through the trailing edge-side cooling passage (67). The third discharge passage (74) discharges a cooling medium flowing through the middle cooling passage (65).

Abstract: A ventilation flow path for guiding a compressed gas flowing between two blade rows adjacent in an axial direction to an interior of a compressor rotor shaft is formed in the compressor rotor shaft. The ventilation flow path has an introduction part, a plurality of branch parts, and a collection part. The introduction part guides the compressed gas flowing between the two blade rows into the compressor rotor shaft. The plurality of branch parts branch out from the introduction part, and are formed in mutually different positions in the axial direction. The collection part is connected to each of the plurality of branch parts. The compressed gas flows into the collection part after passing through the plurality of branch parts, and then, the compressed gas that has flowed in flows outside through the collection part.

Abstract: A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.

Abstract: A rotary machine includes a seal device capable of restricting a flow of a fluid in a clearance between a stationary member and a rotational member. The seal device includes a pressure loss element mounted to the stationary member, a first non-contact type seal protruding from the rotational member toward the pressure loss element and facing the pressure loss element via a first gap, and a second non-contact type seal protruding from the stationary member toward the rotational member, facing the rotational member via a second gap, and being positioned on one side of the pressure loss element in a flow direction of the fluid. The seal device also includes a contact type seal protruding from the stationary member toward the rotational member and being disposed downstream of the pressure loss element and the second non-contact type seal in the flow direction of the fluid.

Abstract: A vane (18) has an airfoil section (19) that extends in a radial direction and an outer shroud (20) that is disposed on the radially outward side of the airfoil section (19), and is supported inside a casing by means of a vane support member (24). The outer shroud (20) has a shroud body (31), radial protrusions (36, 37), and a hook section (32) including the radial protrusions (36, 37) and engaging parts (39, 40). A recessed part (50), which is recessed in an axial direction or in the radial direction, is provided in at least a part of the circumference of the hook section (32). The engaging part (39) has a sealing surface that continues along the entire circumference thereof, the sealing surface coming into contact with the vane support member (24) in the radial direction.

Abstract: A rotor shaft has: an inlet flow passage through which gas inside a gas compression flow passage flows into an outer cavity of a downstream-side cavity group; a radial flow passage that provides communication between the outer cavity and an axial communication cavity of the downstream-side cavity group; an axial flow passage that provides communication between the axial communication cavity of the downstream-side cavity group and the axial communication cavity of an upstream-side cavity group; another radial flow passage that provides communication between the axial communication cavity and the outer cavity of the upstream-side cavity group; and an outlet flow passage through which the gas inside the outer cavity of the upstream-side cavity group flows out into the gas compression flow passage.

Abstract: A ventilation flow path for guiding a compressed gas flowing between two blade rows adjacent in an axial direction to an interior of a compressor rotor shaft is formed in the compressor rotor shaft. The ventilation flow path has an introduction part, a plurality of branch parts, and a collection part. The introduction part guides the compressed gas flowing between the two blade rows into the compressor rotor shaft. The plurality of branch parts branch out from the introduction part, and are formed in mutually different positions in the axial direction. The collection part is connected to each of the plurality of branch parts. The compressed gas flows into the collection part after passing through the plurality of branch parts, and then, the compressed gas that has flowed in flows outside through the collection part.

Abstract: A blade main body (51) of a gas turbine is provided with a first cooling passage part (58), a second cooling passage part (59), a column part (60), and a plurality of protrusions. The first cooling passage part (58) is provided at the side near to a leading edge (55). The second cooling passage part (59) is provided at the side near to a trailing edge (56). The column part (60) is provided between the first cooling passage part (58) and the second cooling passage part (59), and is continuously formed between a base part and an end part of the blade main body (51). The protrusions protrude from the inner wall surfaces of the first cooling passage part (58) and the second cooling passage part (59).

Abstract: An end plate of a blade has a gas path surface facing a combustion gas channel side, an end surface along an edge of the gas path surface, a plurality of channels, and a skirt hole. The plurality of channels extend along the direction of a partial end surface, which is a portion of the end surface, and are arranged in a perspective direction with respect to the partial end surface. The skirt hole opens at the partial end surface. The skirt hole communicates with an inside channel, which is the channel of the plurality of channels that is farthest from the partial end surface.

Abstract: A gas turbine includes a compressor, a turbine, an extraction line, and a component introduction line. A compressed air from an intermediate compression stage of the compressor, as an extraction air, is extracted through the extraction line and is introduced to a first component configuring a portion of the turbine casing through the extraction line. The extraction air, which has passed through the first component, is introduced to a second component serving as a component configuring the turbine through the component introduction line. The second component is a low-pressure component, which is disposed under a pressure environment lower than a pressure of the compressed air at an outlet of the intermediate compression stage.