Mitsubishi Heavy Industries Engine & Turbocharger, Ltd.

Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Eigo Katou

Keigo Sakamoto

Yosuke Dammoto

Yoji Akiyama

Shigeyoshi Sakuma

Nariaki Seike

Takashi Arai

Toyotaka Yoshida

Takeru Chiba

Kenichi Arase

Makoto Ozaki

Daigo Watanabe

Masahiro Nakamura

Eisaku Ito

Noriyuki Hayashi

Masato Takeuchi

Tetsu Konishi

Hiroyuki Arimizu

Yuta Ishii

Hidekatsu Atsumi

Tomoyuki Hirata

Youji Akiyama

Kazuo Ogura

Tomoto Nagai

Yusuke Furuta

Seiji Tsuruoka

Kazuhisa Orimo

Motoharu Ueda

Tsuyoshi Sakurai

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 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 compressor wheel includes a compressor wheel body, and a thermal insulating coating layer disposed so as to cover at least a part of a back surface of the compressor wheel body.

Compressor wheel and supercharger

A turbine housing includes an outer housing portion which includes an inner wall internally forming a spiral space, a first heat shield core which separates the spiral space into a scroll flow passage where an exhaust gas flows and a heat shield space positioned on a side of the inner wall, the first heat shield core being disposed so as to face the inner wall in the spiral space, a variable nozzle unit for adjusting a flow of the exhaust gas from the scroll flow passage toward an impeller, the variable nozzle unit being disposed on a side opposite to the outer housing portion across the first heat shield core in an axial direction, and at least one annular seal portion disposed between the first heat shield core and the outer housing portion in the axial direction.

Turbine housing and turbocharger including the same

A variable nozzle device includes: a first plate-shaped member having a first plate portion having an annular shape and being fixed to a bearing housing; a second plate-shaped member having a second plate portion which has an annular shape and which defines a nozzle flow passage between the first plate portion and the second plate portion, the second plate portion having a surface disposed so as to face the first plate portion and another surface disposed so as to face at least partially a scroll flow passage formed inside a turbine housing; at least one nozzle support having, with respect to an axial direction of the nozzle support, an end coupled to the first plate portion and another end coupled to the second plate portion; at least one nozzle vane rotatably supported between the first plate portion and the second plate portion; and a variable nozzle mechanism configured to change a vane angle of the at least one nozzle vane. The second plate portion is formed to have a larger thickness than the first plate portion.

Variable nozzle device and variable-geometry type exhaust turbocharger

A turbocharger includes: a turbine wheel; a turbine housing; a bearing housing; a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing; a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than a scroll flow path in an axial direction of the turbine wheel; and at least one connection part connecting the mount and the shroud.

Turbocharger

An inner peripheral edge of a first annular member includes a plurality of first inner edge portions belonging to an angular range in which support holes exist in the circumferential direction of a turbine rotor and a plurality of second inner edge portions belonging to an angular range in which the support holes do not exist in the circumferential direction of the turbine rotor. At least one second inner edge portion of the plurality of second inner edge portions comprises a recess portion recessed outward in a radial direction of the turbine rotor, the recess portion extending in an axial direction of the turbine rotor from the side of exhaust gas.

Variable nozzle mechanism and variable geometry turbocharger

The cylinder head includes a plurality of port wall portions configured to form flow paths for intake and exhaust, an outer circumferential wall portion formed in an annular shape disposed at an interval on an outside of the plurality of port wall portions and having a water chamber through which cooling water flows and which is formed at least between the port wall portions and the outer circumferential wall portion, and a bottom wall portion configured to face a combustion chamber of an engine and to connect ends of the port wall portions and the outer circumferential wall portion, wherein the outer circumferential wall portion includes a padding portion of which a thickness is increased toward a side close to the port wall portions so that a distance between the port wall portions and the outer circumferential wall portion is equal to or less than a predetermined distance.

Cylinder head and engine

The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades () are embedded in rotor blade grooves () provided on a rotor disc (), wherein the rotor blade groove () is provided with circular direction grooves () that extend more in the circular direction of the rotor disc than upward from the bottom (), and shaft center direction grooves () that are provided on the end faces () of the rotor disc () in the center of the bottom () in the circular direction of the rotor disc and that extend towards the rotor disc shaft center.

Rotor blade support structure

In a disc axis adjusting mechanism in a gas turbine, the gas turbine has an exhaust gas diffuser provided between a casing wall and a bearing case which are connected to a downstream side of a turbine, a plurality of struts provided at intervals in a circumferential direction, and strut covers coupling an outer diffuser and an inner diffuser of the exhaust gas diffuser so as to cover the struts, and the mechanism comprises: a plurality of air introduction holes formed in the casing wall so as to allow the interior and exterior of the wall to communicate with each other; a sensor unit configured to detect a parameter corresponding to the thermal elongation of each of the struts; and a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes based on a detection value detected by the sensor unit.

Disc axis adjusting mechanism in gas turbine

A gas turbine includes a combustor chamber that houses a combustor unit configured to include a combustor that burns fuel to generate combustion gas for rotating a rotor, a turbine unit chamber that houses a turbine-unit rotor blade and a disk that rotate upon reception of the combustion gas, a combustor casing that forms the combustor chamber, and a casing that is configured to include the combustor casing in which a divided portion on a surface orthogonal to a rotation axis of the rotor is not formed in the combustor casing, but is formed in a portion on a downstream side of flow of the combustion gas lower than the combustor casing.

Gas turbine and method of opening chamber of gas turbine

A gas turbine includes a rotor rotated by combustion gas produced by a combustor that burns fuel, and a casing that is formed by connecting a plurality of casing members divided in plurality, the casing storing the rotor in an inside thereof, and including a second upper-side second vertical inner flange and a third upper-side first vertical inner flange for connecting a second upper casing member with a third upper casing member different from the second upper casing member among the casing members at the inside.

Gas turbine and method for opening chamber of gas turbine

In a gas turbine combustor, a cavity with which a plurality of first air passages communicates is formed by covering with a cover a concave portion of a top hat main body in which the first air passages are formed along the circumferential direction of the top hat main body, a plurality of second fuel passages that communicates with the first fuel passages are formed by connecting an inner ring and an outer ring to the top hat main body and by connecting the inner ring and the outer ring to each other, a peg is fixed on the inner ring to communicate with the second fuel passage through a third air passage, and thin wall portions that serve as a thermal elongation absorbing unit by which thermal elongation is absorbed are provided on the inner ring and the outer ring.

Growing community of inventors

Tokyo, Japan

Eigo Katou