Abstract: A stator blade including a blade body, a first insert, a second insert, and an end cover. The blade body has a first blade air passage and a second blade air passage extending in the blade height direction within the blade body. Each passage has an open end on a blade-height second side. The first insert and the second insert have tubular outer peripheral plate portions. A plurality of impinge holes are formed in the outer peripheral plate portion. The tube height opening side of the outer peripheral plate portion in the tube height direction is open. The outer peripheral plate portion of the first insert is disposed in the first blade air passage such that cooling air flows into the outer peripheral plate portion from the opening of the first insert. The outer peripheral plate portion of the second insert is disposed in the second wing air passage.

Abstract: A turbine blade includes: a pin fin passage formed inside a trailing edge portion of an airfoil part, extending toward a trailing edge of the airfoil part, and opening to outside of the airfoil part at the trailing edge; and a plurality of pin fins connecting a pair of facing inner walls constituting the pin fin passage. The pin fin passage includes a first region and a second region on the trailing edge side of the first region. The plurality of pin fins includes a plurality of first pin fins disposed in the first region and a plurality of second pin fins disposed in the second region. A first diameter of the first pin fins is larger than a second diameter of the second pin fins. A first pin pitch of the first pin fins is larger than a second pin pitch of the second pin fins.

Abstract: A turbine stator vane includes: a blade body having an outer end and an inner end in a blade height direction; a cooling passage extending along the blade height direction inside the blade body; an outer shroud connected to the blade body at the outer end side of the blade body in the blade height direction; an inner shroud connected to the blade body at the inner end side of the blade body in the blade height direction; and an internal passage forming part extending along the blade height direction inside the cooling passage. The internal passage forming part forms an internal passage communicating with each of an outer space on an opposite side to the blade body across the outer shroud and an inner space on an opposite side to the blade body across the inner shroud.

Abstract: A turbine blade includes: a blade body; and a plurality of cooling passages each extending inside the blade body along a blade height direction and are connected to each other via return portions disposed at an end portion in the blade height direction to form a serpentine passage. The cooling passages include: an upstream passage disposed on an upstream side in a flow of a cooling fluid among the plurality of cooling passages; a downstream passage disposed on a downstream side in the flow of the cooling fluid among the plurality of cooling passages; and at least one intermediate passage disposed between the upstream passage and the downstream passage among the plurality of cooling passages. The upstream passage is disposed closest to a leading edge in a chord direction of the blade body among the plurality of cooling passages formed inside the blade body and extending along the height direction.

Abstract: A turbine blade and a gas turbine are provided with: an airfoil portion (41) internally including a cooling air passage (60); a platform (42) provided in a blade base end portion (55) in a blade height direction (Dh) of the airfoil portion (41); and a fillet portion (80) provided around the entire perimeter of a connecting portion of the airfoil portion (41) and the platform (42). The fillet portion (80) includes a first fillet portion (81) which is provided on a rear side blade surface (53) side of the airfoil portion (41), on the trailing edge (52) side of a position at which the distance between the rear side blade surface (53) of the airfoil portion (41) and a rear side edge portion (44) of the platform (42) is shortest, and which has a fillet width (W) that is greater than the fillet width W of other regions of the fillet portion (80).

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 being in communication with each other to define a serpentine flow passage. The plurality of cooling passages include first turbulators on an inner wall surface of an upstream cooling passage of the plurality of cooling passages, and second turbulators on an inner wall surface of a downstream cooling passage of the plurality of cooling passages. A second angle formed by the second turbulators with respect to a flow direction of a cooling fluid in the downstream cooling 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 cooling passage.

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 turbine blade and a gas turbine are provided with: an airfoil portion (41) internally including a cooling air passage (60); a platform (42) provided in a blade base end portion (55) in a blade height direction (Dh) of the airfoil portion (41); and a fillet portion (80) provided around the entire perimeter of a connecting portion of the airfoil portion (41) and the platform (42). The fillet portion (80) includes a first fillet portion (81) which is provided on a rear side blade surface (53) side of the airfoil portion (41), on the trailing edge (52) side of a position at which the distance between the rear side blade surface (53) of the airfoil portion (41) and a rear side edge portion (44) of the platform (42) is shortest, and which has a fillet width (W) that is greater than the fillet width W of other regions of the fillet portion (80).

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 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 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 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.