Abstract: A vane structure for an axial flow turbomachine that has: a single-vane section of a one-vane structure formed in a part in a vane radial direction; and a tandem-vane section which is formed in a remaining part in the vane radial direction continuously with the single-vane section, and which includes a front vane and a rear vane arranged forward and backward with respect to an airflow that flows through a flow path, respectively.

Abstract: The present invention provides a turbine blade that is exposed to a high temperature atmosphere at relatively high temperatures and to a low temperature atmosphere at relatively low temperatures, including: a concave-curve-like pressure surface that is concaved along a flow direction of fluid; a convex-curve-like suction surface that is convexed along the flow direction of the fluid; and a concave and convex formation device which causes a concave and convex portion along the flow of the fluid to appear on the suction surface when the turbine blade is exposed to the low temperature atmosphere, and which turns the suction surface into a smooth surface along a convex curve surface of the suction surface when the turbine blade is exposed to the high temperature atmosphere.

Abstract: A blade surrounded by: a leading edge portion, which is where fluid flows in; a pressure surface which is a concave curve shape concaved along a direction the fluid flows; a suction surface which is a convex curve shape convexed along a direction the fluid flows; and a trailing edge portion, which is where the fluid flows out, in which a disturbance addition portion is provided on the suction surface closer to the leading edge portion than a maximum velocity point, where the flow velocity of the fluid is maximized on the suction surface, for disturbing a laminar flow on the suction surface and for transitioning to a turbulent flow.

Abstract: A wall configuration of an axial-flow machine which can reduce the secondary flow loss is provided. A trough is formed between a blade and another blade in the blade row and extends in at least an axial direction of the blade row. The region where the trough is formed is axially between a leading edge and a trailing edge of the blade. A center line of the trough has a curvature in the same direction as a camber line of the blade. A maximum amplitude of the trough is located adjacent to an axial center of the blade or located axially between the axial center and the leading edge of the blade.

Abstract: The present invention provides a turbine blade that is exposed to a high temperature atmosphere at relatively high temperatures and to a low temperature atmosphere at relatively low temperatures, including: a concave-curve-like pressure surface that is concaved along a flow direction of fluid; a convex-curve-like suction surface that is convexed along the flow direction of the fluid; and a concave and convex formation device which causes a concave and convex portion along the flow of the fluid to appear on the suction surface when the turbine blade is exposed to the low temperature atmosphere, and which turns the suction surface into a smooth surface along a convex curve surface of the suction surface when the turbine blade is exposed to the high temperature atmosphere.

Abstract: A blade surrounded by: a leading edge portion, which is where fluid flows in; a pressure surface which is a concave curve shape concaved along a direction the fluid flows; a suction surface which is a convex curve shape convexed along a direction the fluid flows; and a trailing edge portion, which is where the fluid flows out, in which a disturbance addition portion is provided on the suction surface closer to the leading edge portion than a maximum velocity point, where the flow velocity of the fluid is maximized on the suction surface, for disturbing a laminar flow on the suction surface and for transitioning to a turbulent flow.

Abstract: A wall configuration of an axial-flow machine which can reduce the secondary flow loss is provided. A trough is formed between a blade and another blade in the blade row and extends in at least an axial direction of the blade row. The region where the trough is formed is axially between a leading edge and a trailing edge of the blade. A center line of the trough has a curvature in the same direction as a camber line of the blade. A maximum amplitude of the trough is located adjacent to an axial center of the blade or located axially between the axial center and the leading edge of the blade.

Abstract: A turbine nozzle segment, a turbine nozzle, a turbine, and a gas turbine engine. The turbine nozzle segment is provided with an outer band 39 of an arc shape, an inner band 41 of an arc shape, a thick stator vane 43 in which an insertion hole 49 to which a probe 47 is insertable from a side of the outer band 39 is formed and on the pressure surface 43b of which an inlet hole 51 communicating with the insertion hole 49 is formed, and a thin stator vane 45 having a suction surface 45a having an identical shape to a suction surface 43a of the thick stator vane 43 and a smooth pressure surface 45b approximating to a pressure surface 43b of the thick stator vane 43 configured to be thinner than the thick stator vane.