Abstract: A turbine is provided with: a turbine wheel configured to rotate about an axis O1; a turbine housing accommodating the turbine wheel and defining an annular nozzle passage on the outer peripheral side of the turbine wheel; and a plurality of low solidity nozzle vanes 6 arranged in the nozzle passage at an interval in the circumferential direction. Circumferentially adjacent low solidity nozzle vanes 6 are disposed at different radial positions in a connection position of each of the low solidity nozzle vanes 6 with a hub-side wall surface of the hub-side wall surface and a shroud-side wall surface which define the nozzle passage.

Abstract: A variable nozzle device 20 for a variable geometry turbocharger includes: a nozzle mount 21; a nozzle plate 22 disposed so as to face the nozzle mount, the nozzle plate forming a nozzle flow passage 4 having an annular shape between the nozzle plate 22 and the nozzle mount 21; and a plurality of variable nozzle vanes 6 disposed at a predetermined interval in a circumferential direction of the nozzle flow passage 4 so as to be individually rotatable about a pivot axis O2. The nozzle plate 22 includes a first surface 33 facing the nozzle mount 21, a second surface 34 opposite to the first surface 33, and at least one through hole 36 formed through the first surface 33 and the second surface 35.

Abstract: A variable geometry turbine includes: a turbine rotor; a scroll passage forming part which forms a scroll passage; an exhaust gas passage forming part which forms an exhaust gas passage for introducing an exhaust gas from the scroll passage to the turbine rotor; and a variable nozzle unit including a plurality of nozzle vanes disposed in the exhaust gas passage and configured to be rotatable about respective rotation centers. The exhaust gas passage forming part includes: a first plate member having an annular first plate part; and a second plate member having an annular second plate part which defines the exhaust gas passage between the first plate part and the second plate part and is disposed closer to a turbine outlet than the first plate part in an axial direction of the turbine rotor.

Abstract: A turbine includes: a rotatable impeller with a hub provided with a plurality of rotor blades; and a tubular member in which a diffuser located downstream of the impeller is formed. On an inner surface of the tubular member, a plurality of projections projecting radially inward of the tubular member are formed at positions closer to an inlet end of the tubular member than an outlet end of the tubular member. The plurality of projections are arranged in a circumferential direction of the inner surface so as to leave a space between adjacent projections.

Abstract: A nozzle vane of a variable geometry turbocharger comprises: a nozzle vane body rotatably disposed in an exhaust gas passage defined between a shroud surface and a hub surface; and a fin disposed on at least one of a pressure surface or a suction surface of the nozzle vane body and disposed within a range of 0.6L from a trailing edge of the nozzle vane body, where L refers to a chord length of the nozzle vane body. The fin satisfies a relationship of 0.3L?X, where X refers to a length of the fin along a chord direction of the nozzle vane body.

Abstract: A turbine includes: a rotatable impeller with a hub provided with a plurality of rotor blades; and a tubular member in which a diffuser located downstream of the impeller is formed. On an inner surface of the tubular member, a plurality of projections projecting radially inward of the tubular member are formed at positions closer to an inlet end of the tubular member than an outlet end of the tubular member. The plurality of projections are arranged in a circumferential direction of the inner surface so as to leave a space between adjacent projections.

Abstract: Provided are a variable geometry turbine and a supercharger including the same that can change flow rate characteristics of a turbine in accordance with engine output with simple structure and can adjust the flow angle of a fluid flowing into a turbine impeller to any angle in the circumferential direction of the turbine impeller. The variable geometry turbine (10) includes a turbine impeller (12) configured to rotate about an axis line, a turbine housing (30) configured to accommodate the turbine impeller (12) and form a throat passage (32) and a scroll flow channel (34) on the outer circumferential side of the turbine impeller (12), the scroll flow channel (34) communicating with the throat passage (32), and a width changing mechanism in which a width change portion (52) that changes a passage width of the throat passage (32) along the circumferential direction of the turbine impeller (12) is movable in the width direction of the passage width.

Abstract: A variable nozzle device 20 for a variable geometry turbocharger includes: a nozzle mount 21; a nozzle plate 22 disposed so as to face the nozzle mount, the nozzle plate forming a nozzle flow passage 4 having an annular shape between the nozzle plate 22 and the nozzle mount 21; and a plurality of variable nozzle vanes 6 disposed at a predetermined interval in a circumferential direction of the nozzle flow passage 4 so as to be individually rotatable about a pivot axis 02. The nozzle plate 22 includes a first surface 33 facing the nozzle mount 21, a second surface 34 opposite to the first surface 33, and at least one through hole 36 formed through the first surface 33 and the second surface 35.

Abstract: A turbine is provided with: a turbine wheel configured to rotate about an axis O1; a turbine housing accommodating the turbine wheel and defining an annular nozzle passage on the outer peripheral side of the turbine wheel; and a plurality of low solidity nozzle vanes 6 arranged in the nozzle passage at an interval in the circumferential direction. Circumferentially adjacent low solidity nozzle vanes 6 are disposed at different radial positions in a connection position of each of the low solidity nozzle vanes 6 with a hub-side wall surface of the hub-side wall surface and a shroud-side wall surface which define the nozzle passage.

Abstract: A turbine rotor blade according to at least one embodiment of the present invention is to be connected to a rotational shaft so as to be rotatable around an axis and includes: a hub having a hub surface inclined with respect to the axis in a cross-section along the axis; at least one rotor blade disposed on the hub surface; and a connection passage disposed inside the turbine rotor blade and connecting a first opening disposed in the at least one rotor blade and a second opening disposed downstream of the first opening in the turbine rotor blade.

Abstract: A variable geometry turbocharger (100) includes a bearing housing (10) including a bearing-housing side support portion (40) configured to support a radially outer portion (38) of a nozzle mount (16) from a side opposite to a scroll flow passage (4) in an axial direction of a turbine rotor (2), and wherein at least one of the following condition (a) or (b) is satisfied: (a) the bearing-housing side support portion (40) includes at least one bearing-housing side recess portion (46) formed so as to be recessed in the axial direction so as not to be in contact with the radially outer portion (38); (b) the radially outer portion (38) of the nozzle mount (16) includes at least one nozzle-mount side recess portion (62) formed so as to be recessed in the axial direction so as not to be in contact with the bearing-housing side support portion (40).

Abstract: A nozzle vane for a variable geometry turbocharger satisfies 0.45<(Xp/L)?0.60, where L is a chord length of the nozzle vane, and Xp is a distance between a leading edge of the nozzle vane and a rotation center of the nozzle vane.

Abstract: A nozzle vane of a variable geometry turbocharger comprises: a nozzle vane body rotatably disposed in an exhaust gas passage defined between a shroud surface and a hub surface; and a flange portion provided on at least one of a shroud-side end surface or a hub-side end surface of the nozzle vane body, and formed around a center of rotation of the nozzle vane body.

Abstract: A turbine blade configured to be coupled to a rotational shaft and rotated around an axis includes: a hub having a hub surface which is inclined with respect to the axis in a cross section along the axis; a rotor blade disposed on the hub surface; and at least one rib formed on a blade surface of the rotor blade, the at least one rib extending in a direction which intersects with a span direction of the rotor blade in a meridional plane of the rotor blade.

Abstract: Provided are a variable geometry turbine and a supercharger including the same that can change flow rate characteristics of a turbine in accordance with engine output with simple structure and can adjust the flow angle of a fluid flowing into a turbine impeller to any angle in the circumferential direction of the turbine impeller. The variable geometry turbine (10) includes a turbine impeller (12) configured to rotate about an axis line, a turbine housing (30) configured to accommodate the turbine impeller (12) and form a throat passage (32) and a scroll flow channel (34) on the outer circumferential side of the turbine impeller (12), the scroll flow channel(34) communicating with the throat passage (32), and a width changing mechanism in which a width change portion (52) that changes a passage width of the throat passage (32) along the circumferential direction of the turbine impeller (12) is movable in the width direction of the passage width.

Abstract: A variable displacement exhaust turbocharger according to at least one embodiment comprises: a plurality of nozzle vanes; an annular drive ring; and a lever plate fitted at one end in a groove portion disposed in the drive ring via a connecting pin portion and connected at another end to each nozzle vane. The value of dimensionless slippage S between the groove portion and the connecting pin portion is equal to or less than 0.0016. The dimensionless slippage S is represented by a certain equation.

Abstract: A radial inflow turbine includes a scroll flow passage, a turbine wheel disposed radially inward of the scroll flow passage, a plurality of variable nozzle vanes disposed on a flow passage extending from the scroll flow passage toward the turbine wheel, at a radial position between the scroll flow passage and the turbine wheel, a nozzle mount rotatably supporting each of the plurality of variable nozzle vanes, a nozzle plate arranged to face the nozzle mount and forming the flow passage with the nozzle mount, and a swirl generating member disposed, radially outward of the plurality of variable nozzle vanes, on the nozzle plate in a height range which is smaller than that of a vane height of each of the plurality of variable nozzle vanes. A position of an end part of the swirl generating member on a side of the nozzle mount is farther away from the nozzle mount than a position of an end part of each of the plurality of variable nozzle vanes on the side of the nozzle mount in an axial direction.

Abstract: A nozzle vane for a variable geometry turbocharger has an airfoil including a leading edge, a trailing edge, a pressure surface, and a suction surface at least in a center position in a blade height direction. The airfoil satisfies 0?Wmax/L<0.03, where Wmax is a maximum value of a distance from a line segment connecting the trailing edge and a fixed point on the pressure surface at a 40% chord position from the trailing edge toward the leading edge to a given point on the pressure surface between the trailing edge and the fixed point, and L is a length of the line segment.

Abstract: A nozzle vane of a variable geometry turbocharger comprises: a nozzle vane body rotatably disposed in an exhaust gas passage defined between a shroud surface and a hub surface; and a flange portion provided on at least one of a shroud-side end surface or a hub-side end surface of the nozzle vane body, and formed around a center of rotation of the nozzle vane body.

Abstract: A turbine wheel (12) is provided with: a disc (22) provided so as to be capable of rotating about a center axis (C); and a plurality of blades (23) provided to a disc surface (22f) at intervals in a circumferential direction, the blades (23) causing a gas guided in from radially outward leading edges (23f) to be expelled from trailing edges (23r) disposed on one side of each of the blades along the direction of the center axis (C). In each of the blades (23), in an area on one side along the direction of the center axis (C) including the trailing edge (23r), there is provided a concave surface (27) in which a positive-pressure surface (23p) on the rear side in a rotational direction (R) is recessed forward in the rotational direction (R), causing the gas to be dispersed entirely in the radial direction of the blade (23).