Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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 (40) along a circumferential direction of a rotation shaft and a bend part (52) 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 (30). The bend part includes a tip-side inner wall surface (60) of a bend shape at least in a region at an upstream side, in the axial direction, of a portion (36H) of a leading edge (36) of the turbine blades, the portion being adjacent to a hub.

Abstract: In a scroll structure for a radial turbine configured such that a turbine rotor 02 is rotationally driven by causing exhaust gas to flow from a spiral scroll portion 4 formed in a turbine housing 1 toward a rotor blade 3 of the scroll portion 4 in a radial direction, and act on the rotor blade 3, then flow out in an axial direction, a heat radiation space portion is formed in a shroud portion 11 between the turbine housing 1 and a turbine chamber provided with the rotor blade 3.

Abstract: 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.

Abstract: 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 (40) along a circumferential direction of a rotation shaft and a bend part (52) 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 (30). The bend part includes a tip-side inner wall surface (60) of a bend shape at least in a region at an upstream side, in the axial direction, of a portion (36H) of a leading edge (36) of the turbine blades, the portion being adjacent to a hub.

Abstract: 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.

Abstract: In a turbine scroll part structure of a radial turbine, a flow passage 3 of a connecting part between an exhaust gas inlet into a turbine housing 5 and a scroll part 1 is offset along an axis line L1 of a rotating shaft of a turbine rotor in an amount H, and a cut-out portion P is formed in a tongue portion 2, which separates the flow passage 3 from a blade side passage 4 through which the exhaust gas flows toward blades 6, for the exhaust gas to flow from the flow passage 3 into the blade side passage 4.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An object is to increase portions (increase the amount of correction), where the rotational balance of a rotary shaft of a turbocharging device incorporating an electric motor is adjusted, and to maintain sufficient motor driving force even under a high temperature condition. In a balance adjusting structure for the turbocharging device incorporating an electric motor, a rotor core 5 formed by laminating electromagnetic steel plates 51 is interposed between rotor blades provided on one end or both ends, a rotational balance adjusting member made of iron (magnetic induction member) having a thickens larger than the thickness of each electromagnetic steel plate 51 is disposed on an end of the laminated electromagnetic steel plates 51, or between the laminated layers.

Abstract: 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.

Abstract: 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 scroll 4 has a partition plate 20 a 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 portion 21 formed on the inner periphery of a gas inlet portion of the scroll.