Abstract: A turbine includes a diffuser. The diffuser includes a combustor basket, an outer shell, a plurality of struts, and a protrusion. A front end of the protrusion is between a leading edge position of an adjacent pair of the struts and a trailing edge position of the adjacent pair of the struts, and a rear end of the protrusion extends further than the trailing edge position of the adjacent pair of the struts in an axial direction.

Abstract: A turbine includes a diffuser. This diffuser includes a combustor basket, an outer shell, a plurality of struts, and a protrusion. The protrusion is configured so that a front end thereof located on one side in the direction of the axis is disposed between a leading edge of the strut on the one side in the direction of the axis and a trailing edge of the strut on the other side in the direction of the axis, and a rear end thereof located on the other side in the direction of the axis is disposed farther along in the direction of the axis on the other side than the trailing edge.

Abstract: A combustion burner includes a nozzle and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle. The swirl vane includes a tip portion for swirling gas, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle, the root portion having a cutout on a side of a trailing edge. The radially-outer region and a radially-inner region of the axial flow path communicate with each other, at least in a range in the axial direction in which the swirl vane is disposed. The swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge.

Abstract: A welding device including a cylindrical powder nozzle (201) that supplies a powder gas containing a powder welding material toward a laser beam irradiation position of a base material and a cylindrical shield nozzle (202) that is arranged coaxially so as to cover an outer peripheral surface of the powder nozzle (201) and supplies a shielding gas for isolating the laser beam irradiation position, in which an outer peripheral surface (201b) in the vicinity of a distal end portion (201a) of the powder nozzle (201) has a shape whose outer diameter gradually decreases toward a distal end portion (201a) of the powder nozzle (201) and has an arc-shaped section on a section passing through a center axis (A) of the powder nozzle (201) is provided.

Abstract: The condenser which has a thin heat transfer pipe group, a main body trunk, and an intermediate trunk, and which generates condensed water by causing steam discharged from a steam turbine to flow from an upper section of the intermediate trunk, and by bringing the steam into contact with the thin heat transfer pipe group. In the intermediate trunk, upstream side heaters and downstream side heaters are arranged so as to be parallel to each other in a steam flowing direction. The downstream side heaters and turbine bypass pipes are arranged at the same position in the steam flowing direction. The length of a gap between the upstream side heaters and the downstream side heaters, and the turbine bypass pipes is set to be equal to or shorter than the radius of the turbine bypass pipes.

Abstract: A combustion burner includes a nozzle and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle. The swirl vane includes a tip portion for swirling gas, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle, the root portion having a cutout on a side of a trailing edge. The radially-outer region and a radially-inner region of the axial flow path communicate with each other, at least in a range in the axial direction in which the swirl vane is disposed. The swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge.

Abstract: The condenser which has a thin heat transfer pipe group, a main body trunk, and an intermediate trunk, and which generates condensed water by causing steam discharged from a steam turbine to flow from an upper section of the intermediate trunk, and by bringing the steam into contact with the thin heat transfer pipe group. In the intermediate trunk, upstream side heaters and downstream side heaters are arranged so as to be parallel to each other in a steam flowing direction. The downstream side heaters and turbine bypass pipes are arranged at the same position in the steam flowing direction. The length of a gap between the upstream side heaters and the downstream side heaters, and the turbine bypass pipes is set to be equal to or shorter than the radius of the turbine bypass pipes.

Abstract: A compressor which includes: an inner casing arranged so as to cover a rotor shaft; an outer casing arranged so as to cover the inner casing and forming a fluid flow path around the rotor shaft; and a plurality of struts mounted in the entrance of the fluid flow path and between the inner casing and the outer casing; in which the plurality of struts are arranged in a radial pattern centered on the rotor shaft, and the spacings between the adjacent struts in the circumferential direction of the rotor shaft are unequal.

Abstract: Sectional profiles close to a tip 124 and a part between a midportion 125 and a hub 123 are shifted to the upstream of an operating fluid flow in a sweep direction. Accordingly, an S shape is formed in which the tip 124 and the part between the midportion 125 and the hub 123 protrude. As a result, it is possible reduce various losses due to shook, waves, thereby forming a transonic airfoil having an excellent aerodynamic characteristic.

Abstract: Sectional profiles close to a tip 124 and a part between a midportion 125 and a hub 123 are shifted to the upstream of an operating fluid flow in a sweep direction. Accordingly, an S shape is formed in which the tip 124 and the part between the midportion 125 and the hub 123 protrude. As a result, it is possible reduce various losses due to shook, waves, thereby forming a transonic airfoil having an excellent aerodynamic characteristic.

Abstract: A compressor which includes: an inner casing arranged so as to cover a rotor shaft; an outer casing arranged so as to cover the inner casing and forming a fluid flow path around the rotor shaft; and a plurality of struts mounted in the entrance of the fluid flow path and between the inner casing and the outer casing; in which the plurality of struts are arranged in a radial pattern centered on the rotor shaft, and the spacings between the adjacent struts in the circumferential direction of the rotor shaft are unequal.