Mitsubishi Heavy Industries Limited

Mitsubishi Heavy Industries Engine & Turbocharger, Ltd.

Katsuyuki Osako

Takao Yokoyama

Motoki Ebisu

Takashi Shiraishi

Yasuaki Jinnai

Seiichi Ibaraki

Isao Tomita

Toyotaka Yoshida

Noriyuki Hayashi

Atsushi Matsuo

Takashi Mikogami

Hiroshi Suzuki

Hideaki Arita

Toshihiko Miyake

Yukio Yamashita

Byeongil An

Ryo Takata

Yuki Yamada

Hirotaka Higashimori

Takashi Goto

Daigo Watanabe

Masaki Tojo

Naomichi Shibata

Koji Wakashima

Satomi Nagae

Shozo Maekawa

Ryoji Utsumi

An electric compressor comprising: an electric motor; a rotation shaft configured to be driven by the electric motor; two impellers respectively provided to both ends of the rotation shaft; two housings that respectively contain the two impellers; and an intake manifold pipe configured to branch off from one intake pipe to supply air to each of the two housings. Each of the two housings includes an intake port which opens in a direction intersecting the axial direction of the rotation shaft and to which the intake manifold pipe is connected.

Electric compressor

A motor rotor structure for an electric turbo charger is manufactured at low cost with good quality by fixedly fitting, over a shaft, a rotor core having electromagnetic steel sheets pre-formed as an integrated stack. The rotor structure includes a rotor core which is rotated by a magnetic field formed by a stator in a housing; a shaft configured to rotate a compressor impeller and the rotor core together; and a bearing supporting the shaft. The rotor includes the rotor core including the electromagnetic steel sheets; a stopper portion formed at an intermediate portion of the shaft to restrict axial movement of the rotor core; and a pressing unit which presses the rotor core fitted over the shaft against the stopper portion. The pressing unit prevents a circumferential phase shift between the shaft and the rotor core by a pressing force thereof.

Motor rotor structure for electric turbo charger and method of assembling same

A radial turbine comprises a plurality of nozzle vanes disposed along a circumferential direction inside a spiral scroll and configured to regulate a flow of a working gas from the scroll to a rotor blade, wherein each of the nozzle vane includes a leading edge bulging portion on both end portions in a width direction of an inlet leading edge portion, the leading edge bulging portion being bulged toward a pressure face side of the nozzle vane relative to a central portion, so that a vane angle is configured to correspond with an inflow angle of the working gas to be flown into the nozzle vane, and wherein each of the nozzle vane includes a trailing edge bulging portion on both end portions in a width direction of an outlet trailing edge portion, the trailing edge bulging portion being bulged toward the pressure face side relative to a central portion, so that an outflow angle of the working gas from the outlet trailing edge of the nozzle vane becomes uniform.

Radial turbine

In a variable geometry turbocharger including a variable nozzle mechanism, an object is to enhance safety upon malfunction of the variable nozzle mechanism as well as to improve accuracy in the control of the variable nozzle mechanism by applying a moment that acts on the nozzle vanes in an opening direction securely and stably. A variable geometry turbocharger includes a plurality of nozzle vanesdisposed at predetermined intervals around a rotational shaft center of a turbine wheelso as to surround an outer circumferential side of the turbine wheeland a variable nozzle mechanism configured capable of changing a blade angle of each of the nozzle vanes, each of the nozzle vaneshaving a blade cross-section orthogonal to a nozzle shaftof each nozzle vane, the blade cross-section having: a concave portioncurved into a concave shape on at least a part of a pressure surfaceside, the part being disposed at a trailing edgeside with respect to the rotational center C; and a convex portion at a leading edgeside with respect to the rotational center C, so that a surface shape of the pressure surfaceside is a substantially S-shape having the concave portion and the convex portion across a boundary at a same longitudinal position as the rotational center.

Variable geometry turbocharger

An object is to provide an engine system including an intake bypass device whereby it is possible to expand the operation range of a compressor without causing the output of a turbine to become insufficient. An engine system includes an intake bypass device including a bypass channel connecting a downstream side of a compressor of a turbocharger in an intake channel and an upstream side of a turbine of the turbocharger in an exhaust channel, a bypass valve disposed in the bypass channel and configured to control a flow of compressed intake air in the bypass channel, and a heating unit for heating the compressed intake air flowing through the bypass channel.

Engine system with intake bypass device

An object is to provide an axial flow turbine of radial-inflow type whereby it is possible to suppress a decrease in turbine efficiency due to tip leakage, and a turbocharger having the same. An axial flow turbine of radial-inflow type includes a housing having a scroll part for swirling working fluid flowing into the housing () along a circumferential direction of a rotation shaft and a bend part () for changing a flow direction of the working fluid flowing inwardly in the radial direction from the scroll part into a direction along the axial direction to direct the working fluid to turbine blades (). The bend part includes a tip-side inner wall surface () of a bend shape at least in a region at an upstream side, in the axial direction, of a portion (H) of a leading edge () of the turbine blades, the portion being adjacent to a hub. The bend shape of the tip-side inner wall surface along the axial direction has a minimum curvature radius Rat a position Xnear the turbine blades, and a curvature radius R (&#x3e;R) at the upstream side of the position X.

Radial-inflow type axial flow turbine and turbocharger

In a scroll structure for a radial turbine configured such that a turbine rotoris rotationally driven by causing exhaust gas to flow from a spiral scroll portionformed in a turbine housingtoward a rotor bladeof the scroll portionin a radial direction, and act on the rotor blade, then flow out in an axial direction, a heat radiation space portion is formed in a shroud portionbetween the turbine housingand a turbine chamber provided with the rotor blade

Scroll portion structure for radial turbine or diagonal flow turbine

A turbine rotor of a turbine includes a hub that serves as an axis of rotation, and a plurality of turbine blades. The turbine blades each have a line extending along a shroud-side edge of the turbine blade from the inlet to the outlet as a shroud line. The shroud line includes an entrance-side shroud line La that makes a small change from the inlet toward the outlet in a blade angle with respect to the axis of rotation, a center shroud line Lb that extends from the outlet side of the entrance-side shroud line La and makes a greater change than that of the entrance-side shroud line La, and an exit-side shroud line Lc that extends from the outlet side of the center shroud line Lb to the outlet and makes a smaller change than that of the center shroud line Lb.

Turbine rotor

In a turbine scroll part structure of a radial turbine, a flow passageof a connecting part between an exhaust gas inlet into a turbine housingand a scroll partis offset along an axis line Lof a rotating shaft of a turbine rotor in an amount H, and a cut-out portion P is formed in a tongue portion, which separates the flow passagefrom a blade side passagethrough which the exhaust gas flows toward blades, for the exhaust gas to flow from the flow passageinto the blade side passage

Turbine scroll part structure

Providing a turbine rotor in which the rotational inertia of the turbine rotor can be reduced without changing the geometry of the blade part, whereas the turbine rotor is provided with the rear side surface so that the stress concentration appearing at the root part regarding the hub part on the rear surface side is constrained in order that the strength and the durability of the turbine rotor can be enhanced. A turbine rotor that comprises a hub partconnected to a rotor shaftand a plurality of blade partsformed around the outer periphery of the hub part, the hub part and the blade parts being integrated into one piece, wherein the diameter of the hub partaround the rotation axis L of the rotor shaftgradually increases along the rotation axis direction toward a rear side surfaceon an end side regarding the rotation axis direction; an annular recessis formed annularly around the rotation axis as a rotation center line, on the side of the rear side surfaceof the hub part; the cross-section of the annular recess whose plane includes the rotation axis is configured with a part of the major arc C of an oval shape or an egg shape, the major arc C being formed so that the oval shape or the egged shape is divided by the major axis b as a symmetrical axis of the oval shape or the egged shape; and, the major axis b is placed in the rear side surface

A sheet-metal turbine housing has a scroll part formed by joining opposing scroll members of sheet metal to form a spiral-shaped exhaust gas passage. The housing includes a member on a side of a bearing housing inclosing a bearing supporting a rotation shaft of a turbine rotor blade member on the exhaust side forms an outer side of the turbine rotor blade. Support columns connect the member on the side of the bearing housing with the member on the exhaust side in an axial direction of the turbine and are arranged at intervals on an outer circumference of the turbine. Each support columns may have a cross-sectional shape which includes an upstream corner and a downstream corner in a direction of a gas flow, each of which has an acute angle, so that an upstream surface and a downstream surface are inclined to the gas flow.

Turbine housing

A turbine wheel includes a plurality of blades having a scallop cut-out profile. The scallop cut-out profile is formed by cutting-out a back side wall part of the blade between the suction surface side of a blade part and the pressure surface side of the adjacent blade.

Turbine wheel

In a radial turbine scroll, an operating gas is led to flow in the radial direction from a spiral scroll formed in a turbine casing into turbine moving blades of a turbine rotor, which is positioned on the inner side of the scroll, so as to act on the turbine moving blades, and then led to flow outside in an axial direction, thereby rotatively driving the turbine rotor, wherein the scrollhas a partition platea length of a certain range on a line of a tongue portion formed on the inner periphery of a gas inlet portion or has a reduced height between scroll side walls at an outlet portion of a tongue portionformed on the inner periphery of a gas inlet portion of the scroll.

Structure of radial turbine scroll

An exhaust turbo-supercharger having a high efficiency is provided. The exhaust turbo-supercharger includes therein an exhaust turbine housing including a spiral channel and a turbine-accommodating chamber connected to an innermost peripheral part of the spiral channel; an exhaust turbine provided in the turbine-accommodating chamber so that the axial line of the exhaust turbine is parallel to that of the spiral channel; a shaft that is concentrically connected to one side of the exhaust turbine in the axial line direction; a bearing housing disposed at the side of the exhaust turbine in the axial line direction so as to be adjacent to the exhaust turbine housing; a bearing that is provided in the bearing housing and that rotatably supports the shaft around the axial line; and a heat shield component interposed between the exhaust turbine housing and the bearing housing. The heat shield component constitutes a part disposed near the entrance of the turbine-accommodating chamber, the part being a part of the inner wall surface of the spiral channel. The part composed of the heat shield component, the part being a part of the inner wall surface of the spiral channel, forms a protruding part protruding toward the inside of the channel relative to an upstream part.

Growing community of inventors

Tokyo, Japan

Katsuyuki Osako