Mitsubishi Heavy Industries Engine & Turbocharger, Ltd.

Bipin Gupta

Toyotaka Yoshida

Yosuke Dammoto

Yoji Akiyama

Yuya Nakahara

Sambhav Jain

Takao Yokoyama

Hiroshi Nakagawa

Takeru Chiba

Toru Hoshi

Takashi Yoshimoto

Yuki Yamada

Nao Taniguchi

Youji Akiyama

Toshimitsu Tanaka

Jain Sambhav

Provided are a variable geometry turbine and a turbocharger with the same. The variable geometry turbine is provided with a turbine impeller, a housing, a plurality of nozzle vanes, and a link mechanism. Inside the housing, a link compartment in which the link mechanism is accommodated is formed, the link compartment being separated from a nozzle flow path by a hub-side member having a hub side surface defining the nozzle flow path. The link mechanism and each of the plurality of nozzle vanes are coupled together via a nozzle shaft penetrating through the hub-side member. The hub-side member has at least one communication hole providing communication between the nozzle flow path and the link compartment. When each of the plurality of nozzle vanes is fully opened, the opening of the at least one communication hole on the nozzle flow path side is formed on the inner side radially of the turbine impeller than the leading edge of each of the plurality of nozzle vanes.

Variable geometry turbine and turbocharger with same

A variable geometry turbine includes a variable nozzle unit for adjusting a flow of exhaust gas in an exhaust gas passage for introducing exhaust gas to the turbine rotor. The variable nozzle unit includes a plurality of nozzle vanes disposed in the exhaust gas passage at intervals in the circumferential direction of the turbine rotor. When the exhaust gas passage is divided into a near-tongue region in the vicinity of a tongue portion of the scroll passage and a far-tongue region which is a region other than the near-tongue region, the plurality of nozzle vanes includes at least one near-tongue nozzle vane disposed in the near-tongue region and at least one far-tongue nozzle vane disposed in the far-tongue region. The at least one near-tongue nozzle vane has, in at least one of a leading edge or a trailing edge of the near-tongue nozzle vane, a notch that is cut out to a greater extent than a leading edge or a trailing edge of the far-tongue nozzle vane.

Variable geometry turbine and turbocharger

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. The first plate member has, in a hub-side passage surface of the first plate part facing the exhaust gas passage, at least one groove portion extending from an inner peripheral edge of the first plate part toward an outer peripheral side.

A variable nozzle devicefor a variable geometry turbocharger includes: a nozzle mount; a nozzle platedisposed so as to face the nozzle mount, the nozzle plate forming a nozzle flow passagehaving an annular shape between the nozzle plateand the nozzle mount; and a plurality of variable nozzle vanesdisposed at a predetermined interval in a circumferential direction of the nozzle flow passageso as to be individually rotatable about a pivot axis O. The nozzle plateincludes a first surfacefacing the nozzle mount, a second surfaceopposite to the first surface, and at least one through holeformed through the first surfaceand the second surface. The at least one through holehas a first openingformed on the first surfaceat an inner side of the pivot axis with respect to a radial direction, and a second openingformed on the second surfaceat an outer side of the first openingwith respect to the radial direction or at the same position as the first openingwith respect to the radial direction. Accordingly, as the working fluid 'g' injected from the through holejoins the working fluid G flowing through the nozzle flow passagetoward the turbine wheelthrough the plurality of variable nozzle vanes, the flow of the working fluid G is guided toward the inner surface at the hubside, and thereby it is possible to suppress deviation of flow of the working fluid G toward the shroud, that is, suppress the drift of the working fluid G.

Variable nozzle device, turbine, and turbocharger

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&#x2264;X, where X refers to a length of the fin along a chord direction of the nozzle vane body.

Nozzle vane

A nozzle vane for a variable geometry turbocharger satisfies 0.45&#x3c;(Xp/L)&#x2264;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.

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. The flange portion is formed to satisfy the expression (i): R1&#x3c;R2 or (ii): R4&#x3c;R3, where R1 is the shortest distance from the center of rotation to an outer edge of the flange portion on the trailing edge side and on a suction surface of the nozzle vane, R2 is the shortest distance from the center of rotation to the outer edge of the flange portion on the leading edge side and on the suction surface of the nozzle vane, R3 is the shortest distance from the center of rotation to the outer edge of the flange portion on the leading edge side and on a pressure surface of the nozzle vane, and R4 is the shortest distance from the center of rotation to the outer edge of the flange portion on the trailing edge side and on the pressure surface of the nozzle vane.

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.

Radial inflow turbine and turbocharger

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&#x2264;W/L&#x3c;0.03, where Wis 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.

A turbine includes: a turbine impeller; a housing disposed so as to enclose the turbine impeller, and including a scroll passage positioned on an outer circumferential side of the turbine impeller and an inner circumferential wall part defining an inner circumferential boundary of the scroll passage; a plurality of nozzle vanes disposed inside an intermediate flow passage which is positioned, in an exhaust gas flow direction, on a downstream side of the scroll passage and on an upstream side of the turbine impeller; and a plate disposed on a side of the intermediate flow passage with respect to the inner circumferential wall part so as to face the intermediate flow passage such that a gap is formed between the plate and the inner circumferential wall part in an axial direction. The plate has at least one through hole through which the intermediate flow passage and the gap are communicated with each other. The at least one through hole opens to a surface of the plate facing the intermediate flow passage, at a position on a radially outer side with respect to a suction surface of at least one of the plurality of nozzle vanes.

Turbine and turbocharger

A turbine for a turbocharger includes: a turbine impeller coupled to a compressor impeller via a rotational shaft; a turbine casing disposed so as to cover the turbine impeller, the turbine casing including a scroll flow passage and a scroll outlet portion disposed on an inner side, in a radial direction, of the scroll flow passage, for guiding exhaust gas from the scroll flow passage to the turbine impeller; and a back-surface side member disposed so as to face a back surface of the turbine impeller. The back-surface side member includes a protruding portion disposed on an impeller facing surface which faces the back surface of the turbine impeller, the protruding portion protruding toward the back surface and extending in a circumferential direction.

Turbine for turbocharger, and turbocharger

Provided is a casingfor an exhaust turbocharger turbine, configured so as to house a turbine rotorto be driven by exhaust gas and form a spiral scrollserving as a path for supplying the exhaust gas to the turbine rotor, wherein the scrollincludes a first regionextending from a spiral origin positionto a predetermined angle &#x3b8; and a second regionextending from the predetermined angle &#x3b8; to a spiral end position, with the surface area of an interior wall thereof decreasing from the spiral origin positiontoward the spiral end position, and the interior wall at the first regionhas a lower surface roughness than that at the second region

Casing for exhaust turbocharger turbine, exhaust turbocharger turbine, and manufacturing method thereof

A turbine includes: a turbine impeller; a housing disposed so as to enclose the turbine impeller and including a scroll passage positioned on an outer circumferential side of the turbine impeller; a nozzle vane disposed inside an intermediate flow passage which is positioned, in an exhaust gas flow direction, on a downstream side of the scroll passage and on an upstream side of the turbine impeller; a plate disposed on a side of the intermediate flow passage with respect to an inner circumferential wall part of the housing, defining an inner circumferential boundary of the scroll passage, so as to face the intermediate flow passage such that a gap is formed between the plate and the inner circumferential wall part in an axial direction; and at least one guide vane disposed in the gap between the inner circumferential wall part and the plate in the axial direction. The at least one guide vane includes: a first end; and a second end disposed radially on an outer side of the first end and circumferentially downstream of the first end in the exhaust gas flow direction.

A turbocharger includes: a turbine wheel; a hub-side wall surface and a shroud-side wall surface which face each other and which together form a flow path for exhaust gas to flow into the turbine wheel; and a nozzle vane which has a shroud-side end surface facing the shroud-side wall surface and a hub-side end surface facing the hub-side wall surface and which is rotatably disposed in the flow path. The nozzle vane has a pressure surface which is, at least on a shroud side, oblique toward a downstream side of the exhaust gas with a distance in a vane height direction from the shroud-side end surface.

Turbocharger, nozzle vane for turbocharger, and turbine

A turbocharger includes a turbine wheel, a hub-side wall surface and a shroud-side wall surface which face each other and which together form a flow path for exhaust gas to flow into the turbine wheel, and a plurality of nozzle vanes each of which is rotatably disposed on one of the hub-side wall surface or the shroud-side wall surface in the flow path. A throat formed between adjacent two of the plurality of nozzle vanes has a narrower throat width at a position of a first end surface of each of the adjacent two nozzle vanes facing the other of the hub-side wall surface or the shroud-side wall surface than a throat width at a middle position between the first end surface and a second end surface on an opposite side to the first end surface of each of the adjacent two nozzle vanes.

Growing community of inventors

Tokyo, Japan

Bipin Gupta