Abstract: A non-positive displacement type pressurizing device for pressurizing a fluid includes a rotor including a rotary blade row including a plurality of rotary blades provided at intervals in a circumferential direction; a casing that accommodates the rotor; a stationary blade row supported by the casing and including a plurality of stationary blades provided at intervals in the circumferential direction; and a plurality of heat exchanging units for cooling the fluid, wherein the heat exchanging units are configured to divide a flow path formed between stationary blades, of the plurality of stationary blades, adjacent to one another in the circumferential direction in a height direction of the stationary blades.

Abstract: An axial flow rotating machine includes: a rotor; a plurality of vanes; and a medium flow modification member. Each of the vanes has an inner shroud and one or more seal fins. An annular groove, which is recessed toward a radially inner side, in which the inner shroud and the seal fins are placed in a non-contact manner, is formed at a rotor shaft. A distance from an end of the inner shroud on a furthest axially downstream side to a downstream-side groove side surface is a distance (L). A distance (Lf) from a most-downstream seal fin to a medium flow modification surface is equal to or less than the distance (L) in the axially downstream side.

Abstract: To provide an axial flow turbine that can reduce interference loss and secondary flow loss, and can reduce mixing loss. An axial flow turbine includes: stator blades provided on the inner-circumference side of a diaphragm outer ring; a diaphragm inner ring provided on the inner-circumference side of the stator blades; moving blades provided on the outer-circumference side of a rotor; a shroud provided on the outer-circumference side of the moving blades; a main flow path constituted by a flow path formed between an inner circumferential surface of the diaphragm outer ring and an outer circumferential surface of the diaphragm inner ring, and a flow path formed between an inner circumferential surface of the shroud and an outer circumferential surface of the rotor; and a cavity formed between the diaphragm inner ring and the rotor. The outer circumferential surface of the rotor has protruding portions and depressed portions.

Abstract: To provide an axial flow turbine that can reduce circumferential pressure differences to reduce loss. The axial flow turbine includes: stator blades arrayed in the circumferential direction; and a diaphragm inner ring having an outer circumferential surface that interconnects the stator blades on their inner-circumference side and constitutes a wall surface of a main flow path. The outer circumferential surface of the diaphragm inner ring has depressed portions. Each depressed portion is formed in an area that is on the downstream side of a throat where the distance between a suction surface of one stator blade of a pair of adjacent blades and a pressure surface of other stator blade of the pair of adjacent blades becomes the shortest, and that lies in the circumferential direction within a range of a throat position on the suction surface of the one stator blade to a downstream edge position of the one stator blade.

Abstract: An axial flow rotating machine includes: a rotor; a plurality of vanes; and a medium flow modification member. Each of the vanes has an inner shroud and one or more seal fins. An annular groove, which is recessed toward a radially inner side, in which the inner shroud and the seal fins are placed in a non-contact manner, is formed at a rotor shaft. A distance from an end of the inner shroud on a furthest axially downstream side to a downstream-side groove side surface is a distance (L). A distance (Lf) from a most-downstream seal fin to a medium flow modification surface is equal to or less than the distance (L) in the axially downstream side.

Abstract: An axial turbine includes an upstream turbine stage that includes: a cover disposed at a distal end of an upstream bucket and opposed to an inner wall of an upstream diaphragm outer ring across a gap; and a downstream diaphragm outer ring that is disposed downstream of the upstream turbine stage and that has an inner peripheral-side end wall shaped into a flare. The inner peripheral-side end wall of the downstream diaphragm outer ring has a flare angle formed to be greater than a slant angle of an inner peripheral-side wall of the cover. In the axial turbine, the inner peripheral-side end wall of the downstream diaphragm outer ring is formed to have a meridional shape that has at least one inflection point between the upstream turbine stage and a downstream turbine stage and such that a tangent at the inflection point with respect to a steam flow direction has a positive gradient.

Abstract: A turbine includes a turbine rotor, a stationary body that covers the turbine rotor, and a diffuser provided on an outlet side of the stationary body. Last-stage moving blades of the turbine rotor include blade sections and covers provided at distal ends of the blade sections. The diffuser is formed such that an outer circumferential surface of an inlet section is small in diameter with respect to an inner circumferential surface of an outlet section of the stationary body and a circumferential wall section of the inlet section at least partially overlaps the covers in a radial direction when viewed from the axial direction. An annular gap space between the stationary body and the covers faces a space on an outer side of an outer circumferential surface of the diffuser when viewed from the axial direction.

Abstract: A moving blade 21d is disposed in a last stage closest to a diffuser 10 among a plurality of stages of a turbine 9 including a turbine rotor 12 and a stationary body 14. The diffuser 10 is connected to an outlet side of the stationary body 14. A distal end of the moving blade 21d is opposed to a seal fin 38 provided in the stationary body 14. The moving blade 21d includes a blade section 26, a cover 27 and a guide 32 provided on a moving blade distal end face 31, which is a surface of the cover 27. The moving blade distal end face 31 extends in a rotation axis direction of the turbine rotor 12, and the guide 32 includes a guide surface 41 located on a side close to the diffuser 10 with respect to the seal fin 38 and formed to incline upward in a direction from the seal fin 38 toward the diffuser 10.

Abstract: An axial turbine includes an upstream turbine stage that includes: a cover disposed at a distal end of an upstream bucket and opposed to an inner wall of an upstream diaphragm outer ring across a gap; and a downstream diaphragm outer ring that is disposed downstream of the upstream turbine stage and that has an inner peripheral-side end wall shaped into a flare. The inner peripheral-side end wall of the downstream diaphragm outer ring has a flare angle formed to be greater than a slant angle of an inner peripheral-side wall of the cover. In the axial turbine, the inner peripheral-side end wall of the downstream diaphragm outer ring is formed to have a meridional shape that has at least one inflection point between the upstream turbine stage and a downstream turbine stage and such that a tangent at the inflection point with respect to a steam flow direction has a positive gradient.

Abstract: A supersonic turbine moving blade in which increased circumferential speed due to increased blade length and average diameter reduces shock wave loss in its inflow area. It has at least one of the following features: pressure surface curvature is nonnegative from the leading to trailing edge end; negative pressure surface curvature is positive upstream and negative downstream; dimensionless pressure surface curvature (inter-blade pitch divided by curvature radius) is larger than 0.0 and smaller than 0.1 in the 30%-to-60% portion of the length along the pressure surface; the leading edge part is formed by continuous curvature curves and the distance between ½ point of the blade maximum thickness and leading edge end exceeds ½ of the maximum thickness; the exit angle is larger than a theoretical outflow angle; and the maximum thickness point is nearer to the trailing edge than to the leading edge.

Abstract: Suppressing profile loss of a moving blade due to radial flow without an increase in the length of a shaft of a turbine is disclosed. The degree of reaction on an inner circumferential side is set to an appropriate degree, reducing profile loss due to supersonic inflow, and improving turbine efficiency. A steam turbine stator vane has a trailing edge with a curved line when the stator vane is viewed from a downstream side in the axial direction. The curved line has an inflection point located on an outer circumferential side with respect to the center of the stator vane in the height direction of the stator vane. An inner circumferential portion of the curved line is located on the inner circumferential side with respect to the inflection point. An outer circumferential portion of the curved line is located on the outer circumferential side with respect to the inflection point.

Abstract: A turbine bucket for a steam turbine low-pressure final stage has an exhaust area exceeding 9.6 m2 and 13.8 m2 in steam-turbine final-stage buckets for a rated speed 3600 rpm and 300 rpm machines, respectively. The turbine bucket is made of martensite steel. A blade portion of the turbine bucket has a suction surface 7 and a pressure surface 8 which are each formed, at a turbine blade root, of three areas consisting of a steam inlet side area 12 with curvature, a steam outlet side area 13 with curvature and an approximately straightly formed area located between the two areas.

Abstract: The axial-flow turbine includes an extraction chamber 15 disposed on the outer circumference of a turbine blade chamber 12 and an extraction opening 16. An outer diaphragm 8 forming the downstream-side wall surface of the extraction chamber 15 is provided with a projection 21 formed more radially inwardly than the downstream-side edge on the outer circumference of an adjacent bucket 2 on the upstream side of the extraction opening 16 to form the downstream-side wall surface of the extraction opening 16. The projection 21 forms an upstream-side wall surface 18 of the outer diaphragm 8 for leading a part of the working fluid to the extraction chamber 15, and an inner wall surface 19 of the outer diaphragm 8 for leading the remaining working fluid to a bucket 11 on the downstream side of the extraction opening 16.

Abstract: A supersonic turbine moving blade in which increased circumferential speed due to increased blade length and average diameter reduces shock wave loss in its inflow area. It has at least one of the following features: pressure surface curvature is nonnegative from the leading to trailing edge end; negative pressure surface curvature is positive upstream and negative downstream; dimensionless pressure surface curvature (inter-blade pitch divided by curvature radius) is larger than 0.0 and smaller than 0.1 in the 30%-to-60% portion of the length along the pressure surface; the leading edge part is formed by continuous curvature curves and the distance between ½ point of the blade maximum thickness and leading edge end exceeds ½ of the maximum thickness; the exit angle is larger than a theoretical outflow angle; and the maximum thickness point is nearer to the trailing edge than to the leading edge.

Abstract: A method of operating an axial turbine, having a stage including stationary blades and moving blades, each stationary blade having a radial height of an outlet thereof higher than the radial height of an inlet thereof, each moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, the moving blades being constructed such that a moving blade front-end peripheral velocity Mach number exceeds 1.0, the method including restraining a radial velocity component of a working fluid flowing through an outer peripheral portion of the stationary blade from the stationary blade inlet to the stationary blade outlet, whereby the working fluid having passed through the stationary blade flows substantially parallel to the central axis of the turbine from the stationary blade outlet to the moving blade inlet.

Abstract: Suppressing profile loss of a moving blade due to radial flow without an increase in the length of a shaft of a turbine is disclosed. The degree of reaction on an inner circumferential side is set to an appropriate degree, reducing profile loss due to supersonic inflow, and improving turbine efficiency. A steam turbine stator vane has a trailing edge with a curved line when the stator vane is viewed from a downstream side in the axial direction. The curved line has an inflection point located on an outer circumferential side with respect to the center of the stator vane in the height direction of the stator vane. An inner circumferential portion of the curved line is located on the inner circumferential side with respect to the inflection point. An outer circumferential portion of the curved line is located on the outer circumferential side with respect to the inflection point.

Abstract: An axial turbine includes a plurality of stages each comprising a plurality of stationary blades arranged in a row along the turbine circumferential direction and a plurality of moving blades in a row parallel to the stationary blades, each of the moving blade being disposed downstream of a respective one of the corresponding stationary blade in a flow direction of a working fluid so as to be opposed to the corresponding stationary blade. Herein, each of the stationary blades is formed so that the intersection line between the outer peripheral portion of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer peripheral portion of the stationary blade and that is parallel to the turbine central axis.

Abstract: An axial turbine includes a plurality of stages each comprising a plurality of stationary blades arranged in a row along the turbine circumferential direction and a plurality of moving blades in a row parallel to the stationary blades, each of the moving blade being disposed downstream of a respective one of the corresponding stationary blade in a flow direction of a working fluid so as to be opposed to the corresponding stationary blade. Herein, each of the stationary blades is formed so that the intersection line between the outer peripheral portion of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer peripheral portion of the stationary blade and that is parallel to the turbine central axis.

Abstract: The axial-flow turbine includes an extraction chamber 15 disposed on the outer circumference of a turbine blade chamber 12 and an extraction opening 16. An outer diaphragm 8 forming the downstream-side wall surface of the extraction chamber 15 is provided with a projection 21 formed more radially inwardly than the downstream-side edge on the outer circumference of an adjacent bucket 2 on the upstream side of the extraction opening 16 to form the downstream-side wall surface of the extraction opening 16. The projection 21 forms an upstream-side wall surface 18 of the outer diaphragm 8 for leading a part of the working fluid to the extraction chamber 15, and an inner wall surface 19 of the outer diaphragm 8 for leading the remaining working fluid to a bucket 11 on the downstream side of the extraction opening 16.

Abstract: An axial turbine includes a plurality of stages, each of the plurality of stages having stationary blades adjacent to each other along the turbine circumferential direction and corresponding moving blades adjacent to each other along the circumferential direction, each of the moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, so as to be opposed to the corresponding stationary blade. In this axial turbine, each of the stationary blades is formed so that the intersection line between the outer periphery of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer periphery of the stationary blade and that is parallel to the central axis of the turbine.