Mitsubishi Heavy Industries Engine & Turbocharger, Ltd.

Mitsubishi Heavy Industries Limited

Yoji Akiyama

Yosuke Dammoto

Toyotaka Yoshida

Bipin Gupta

Eigo Katou

Keigo Sakamoto

Yosuke Danmoto

Takao Yokoyama

Takaya Futae

Yuya Kojima

Nariaki Seike

Yuya Nakahara

Shigeyoshi Sakuma

Takeru Chiba

Toru Hoshi

Tadasuke Nishioka

Takashi Nambu

Tatsuya Ishizaki

Sambhav Jain

Hiroshi Suzuki

Isao Tomita

Motoki Ebisu

Yuki Yamada

Makoto Ozaki

Tadashi Kanzaka

Shuichi Isayama

Hiroyuki Arimizu

Seigi Yano

Jain Sambhav

Tsuyoshi Sakurai

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.

Variable displacement exhaust turbocharger

A nozzle component according to at least one embodiment of the present disclosure is a nozzle component included in a variable nozzle mechanism of a variable geometry turbocharger. The nozzle component is composed of an iron-based alloy and satisfying the following relational expression: 6.6×A+B≥8.0, where A is a total value (mass %) of carbon content and nitrogen content, and B is a total value (mass %) of 0.5 times tungsten content and molybdenum content. The total value B is 1.5 mass % or more.

Nozzle component, variable nozzle mechanism of variable geometry turbocharger, variable geometry turbocharger, and method of producing nozzle component

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 device according to some embodiments includes an annular nozzle plate, an annular nozzle mount defining a nozzle flow passage between the nozzle mount and one surface of the nozzle plate, at least one nozzle support coupling the nozzle plate and the nozzle mount, and fixed to at least the nozzle plate by caulking, and at least one nozzle vane supported between the nozzle plate and the nozzle mount. The nozzle plate has a through hole into which an end portion of the at least one nozzle support is inserted. The through hole includes a straight portion extending from the one surface toward another surface of the nozzle plate, an enlarged diameter portion formed on a side of the another surface of the nozzle plate and having a larger diameter than the straight portion, and a relief processing portion which is formed in a part of the straight portion continuing into the enlarged diameter portion and has a larger diameter than another part of the straight portion where the relief processing portion is not formed.

Nozzle device and exhaust turbocharger

A centrifugal compressor (P) is provided with: a casing () which forms an impeller inlet flow path (), an impeller flow path (), an impeller outlet flow path (), and a scroll (); and an impeller () which is arranged in the impeller flow path (), wherein the casing () is provided with a casing body () and a heat conduction inhibiting part () which is disposed to heat conduction paths to the impeller inlet flow path () from at least the impeller outlet flow path () and the scroll () so as to inhibit heat conduction to the impeller inlet flow path () from at least the impeller outlet flow path () and the scroll ().

Centrifugal compressor and supercharger

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

Variable geometry turbocharger

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 wheel () is provided with: a disc () provided so as to be capable of rotating about a center axis (C); and a plurality of blades () provided to a disc surface () at intervals in a circumferential direction, the blades () causing a gas guided in from radially outward leading edges () to be expelled from trailing edges () disposed on one side of each of the blades along the direction of the center axis (C). In each of the blades (), in an area on one side along the direction of the center axis (C) including the trailing edge (), there is provided a concave surface () in which a positive-pressure surface () 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 ().

Impeller, turbocharger, and method for forming flow field for gas in impeller and turbocharger

There is provided a turbine wheel includes a plurality of long blades and a plurality of short blades. A trailing edge of each short blade is positioned upstream of a trailing edge of each long blade in an axial direction of the turbine wheel, and at least one of a leading edge of each long blade or a leading edge of each short blade includes an inclined part which is inclined so that a distance to a rotational axis of the turbine wheel decreases toward a hub.

Turbine wheel, turbine, 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

The present invention improves the drainability of lubricating oil at a thrust bearing. The present invention comprises: a rotating shaft; a thrust bearing that is provided to the rotating shaft and restricts the axial-direction movement of the rotating shaft; and an oil reservoir part () that has formed therein an oil reservoir space () that is provided to be adjacent to the thrust bearing in the axial direction and to open downward, the oil reservoir space () having formed therein an inclined surface () that, in a region that is in and below a horizontal plane H that passes through the center of the rotating shaft, protrudes to the thrust bearing side and is inclined along the rotational direction of the rotating shaft.

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Tokyo, Japan

Yoji Akiyama