Abstract: A turbine rotor blade includes: a blade body including a pressure surface and a suction surface; and a tip shroud on a tip portion of the blade body, the tip shroud being inclined outward in a radial direction from the pressure surface to the suction surface in an axial direction. The tip shroud includes a fin at a center portion in a circumferential direction, the fin extending radially outward, a pressure-side tip shroud on the pressure surface side, and a suction-side tip shroud. The suction-side tip shroud includes a suction-side contact block at a front edge end of the tip shroud. The pressure-side tip shroud includes a pressure-side contact block at a rear edge end of the tip shroud, the suction-side contact block includes a first surface facing in the circumferential direction, and the pressure-side contact block includes a second surface facing in a direction opposite to the circumferential direction.

Abstract: A turbine rotor blade includes a blade body including a pressure-side blade wall and a suction-side blade wall. The blade body includes: a serpentine passage composed of a cooling passage separated into a plurality of parts by a partition wall that connects the pressure-side blade wall and the suction-side blade wall and extends along a height direction of the blade body; and a first cooling hole communicating at one end with the cooling passage via a first inlet opening formed in an inner wall surface of the pressure-side blade wall or the suction-side blade wall, and communicating at another end with a first outlet opening formed in an outer wall surface of the pressure-side blade wall or the suction-side blade wall of the blade body. The first cooling hole extends in a leading edge direction from the first inlet opening to the first outlet opening.

Abstract: A control device controls a temperature of a shaft seal portion provided around a rotating shaft of a rotating machine to an appropriate temperature by adjusting an amount of the cooling air to be supplied to the shaft seal portion. The control device calculates a sensitivity indicated using the temperature of the shaft seal portion with respect to a flow rate of the cooling air supplied to the shaft seal portion and controls the flow rate of the cooling air so that the sensitivity has a predetermined target value on the basis of the calculated sensitivity. When the sensitivity is calculated, the flow rate is varied in a predetermined range having a certain flow rate as a center. The sensitivity of the temperature at the flow rate as a center is calculated from the variation in the temperature of the shaft seal portion with respect to the variation in the flow rate.

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 turbine blade includes an airfoil body, and a plurality of cooling passages extending along a blade height direction inside the airfoil body and communicating with each other to form a serpentine flow passage. The cooling passages include first turbulators disposed on an inner wall surface of an upstream side passage of the plurality of cooling passages, and second turbulators disposed on an inner wall surface of a downstream side passage of the plurality of cooling passages, the second turbulators being arranged on a downstream side of the upstream side passage. A second angle formed by the second turbulators with respect to a flow direction of a cooling fluid in the most downstream passage is smaller than a first angle formed by the first turbulators with respect to the flow direction of the cooling fluid in the upstream side passage.

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 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: A plurality of circumferential blowout passages that communicate with a cavity into which cooling air flows and that open in a circumferential end surface are formed in a shroud of a vane. Of a central region of the circumferential end surface, an upstream-side region of the circumferential end surface, and a downstream-side region of the circumferential end surface, at least the central region has openings of the plurality of circumferential blowout passages formed therein. A density that is the number of the openings of the circumferential blowout passages per unit length in an axial direction is highest in the central region.

Abstract: A blade includes a blade body with a cooling flow passage through which a cooling medium is configured to flow. The blade body includes a top plate, and a thinning which is defined on a top surface of the top plate, closer to a suction side than a camber line, and which protrudes and extends along the camber line. A top plate flow passage is defined inside the top plate and includes an inlet flow passage which is closer to the suction side than the camber line and into which the cooling medium is configured to flow, a main flow passage which extends in a direction intersecting the camber line along the top surface, and an outlet flow passage through which the cooling medium is configured to be discharged to an outside of the blade body from a position closer to a pressure side than the camber line.

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 blade has a flow passage forming plate that defines a part of a combustion gas flow passage. The flow passage forming plate has a plurality of back channels that open in a back end surface. A density of openings of the plurality of back channels in a middle region of the back end surface is higher than the density of openings of the plurality of back channels in at least one side region of a suction-side region and a pressure-side region of the back end surface. The density of openings is a ratio of a length of wetted perimeter of the plurality of back channels to an interval of openings of the plurality of back channels.

Abstract: An insert assembly (79) includes an insert (80), a reinforcing member (85), and a retaining member (90). The insert (80) is fixed to an end of an airfoil body (51) on one side in a radial direction. The reinforcing member (85) is disposed adjacent to an end of the insert (80) on the other side in the radial direction and enhances the rigidity of the insert (80). The retaining member (90) is fixed to an end of the airfoil body (51) on the other side in the radial direction, and allows the insert (80) to be positioned relative to the airfoil body (51) in a direction orthogonal to the radial direction.

Abstract: Provided is a flow path forming plate having a gas path surface that comes in contact with combustion gas, end surfaces formed at peripheral edges of the gas path surface, a first side passage, and a plurality of end surface blow-out passages. The first side passage extends in a direction along a first end surface that is one of the end surfaces, and cooling air flows through the first side passage. A plurality of passage forming surfaces forming the first side passage includes a first forming surface that faces an opposite-flow-path side and extends gradually farther away from the gas path surface while extending toward the first end surface. The end surface blow-out passages open in the first forming surface of the first side passage and in the first end surface.

Abstract: A first-stage stationary vane of a gas turbine includes: a vane portion including a pressure surface and a suction surface; a shroud wall portion which connects to an end portion of the vane portion and which forms a flow passage wall; a pressure-surface side fillet portion disposed on a corner portion formed by the pressure surface and a wall surface of the shroud wall portion; and a suction-surface side fillet portion disposed on a corner portion formed by the suction surface and the wall surface of the shroud wall portion. The pressure-surface side fillet portion and the suction-surface side fillet portion are separated at a leading-edge side of the vane portion so as not to connect to each other.

Abstract: A blade has a blade, passage extending in a blade height direction, a platform passage formed inside a platform, and a communication passage leading from an outer surface of a shaft-mounted part through the platform passage to the blade passage. An inner surface defining an inflow passage portion of the platform passage includes a shaft-side inner surface that faces a gas path side. The shaft-side inner surface spreads in a direction having more of a component of a blade thickness direction than a component of the blade height direction. An inner surface defining the communication passage joins to the shaft-side inner surface.

Abstract: A blade includes a blade body in which a cooling flow passage through which a cooling medium flows is formed. The blade body includes a top plate, and a thinning which is formed on a top surface of the top plate, closer to a suction side than a camber line, and which protrudes and extends along the camber line. A top plate flow passage is formed inside the top plate. The top plate flow passage includes an inlet flow passage which is formed closer to the suction side than the camber line and into which the cooling medium flows, a main flow passage which extends in a direction intersecting the camber line along the top surface, and an outlet flow passage through which the cooling medium is discharged to an outside of the blade body from a position closer to a pressure side than the camber line.

Abstract: Provided is a flow path forming plate having a gas path surface that comes in contact with combustion gas, end surfaces formed at peripheral edges of the gas path surface, a first side passage, and a plurality of end surface blow-out passages. The first side passage extends in a direction along a first end surface that is one of the end surfaces, and cooling air flows through the first side passage. A plurality of passage forming surfaces forming the first side passage includes a first forming surface that faces an opposite-flow-path side and extends gradually farther away from the gas path surface while extending toward the first end surface. The end surface blow-out passages open in the first forming surface of the first side passage and in the first end surface.

Abstract: An insert assembly (79) includes an insert (80), a reinforcing member (85), and a retaining member (90). The insert (80) is fixed to an end of an airfoil body (51) on one side in a radial direction. The reinforcing member (85) is disposed adjacent to an end of the insert (80) on the other side in the radial direction and enhances the rigidity of the insert (80). The retaining member (90) is fixed to an end of the airfoil body (51) on the other side in the radial direction, and allows the insert (80) to be positioned relative to the airfoil body (51) in a direction orthogonal to the radial direction.

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.