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公开(公告)号：US09011097B2
公开(公告)日：2015-04-21
申请号：US13264610
申请日：2010-07-28
CPC分类号： F01D5/048 , F01D1/28 , F05D2220/40 , F05D2240/307 , F05D2250/70 , F05D2260/20
摘要： 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.
摘要翻译： 涡轮机叶轮包括具有扇形切口轮廓的多个叶片。 扇形切割轮廓通过在叶片部分的吸力表面侧和相邻叶片的压力表面侧之间切割叶片的后侧壁部而形成。
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公开(公告)号：US20130004321A1
公开(公告)日：2013-01-03
申请号：US13264610
申请日：2010-07-28
IPC分类号： F01D5/14
CPC分类号： F01D5/048 , F01D1/28 , F05D2220/40 , F05D2240/307 , F05D2250/70 , F05D2260/20
摘要： 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.
摘要翻译： 涡轮机叶轮包括具有扇形切口轮廓的多个叶片。 扇形切割轮廓通过在叶片部分的吸力表面侧和相邻叶片的压力表面侧之间切割叶片的后侧壁部而形成。
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公开(公告)号：US20120183406A1
公开(公告)日：2012-07-19
申请号：US13256151
申请日：2010-08-10
IPC分类号： F01D5/30
CPC分类号： F01D5/048 , F01D5/026 , F01D5/063 , F05D2230/232 , F05D2250/14 , F05D2250/293 , F05D2260/941
摘要： 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 part 9 connected to a rotor shaft 19 and a plurality of blade parts 11 formed around the outer periphery of the hub part 9, the hub part and the blade parts being integrated into one piece, wherein the diameter of the hub part 9 around the rotation axis L of the rotor shaft 19 gradually increases along the rotation axis direction toward a rear side surface 7 on an end side regarding the rotation axis direction; an annular recess 21 is formed annularly around the rotation axis as a rotation center line, on the side of the rear side surface 7 of the hub part 9; 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 7.
摘要翻译： 提供一种涡轮转子，其中可以在不改变叶片部分的几何形状的情况下减小涡轮转子的旋转惯性，而涡轮转子设置有后侧表面，使得在根部处出现的关于轮毂部分的应力集中 在后表面侧受到限制，以提高涡轮转子的强度和耐久性。 涡轮转子，其包括连接到转子轴19的毂部9和围绕毂部9的外周形成的多个叶片部11，轮毂部和叶片部一体地形成为一体，其中， 转子轴19的旋转轴线L周围的轮毂部9沿着旋转轴线方向朝向相对于旋转轴方向的端侧的后方侧面7逐渐增大; 环形凹部21在轮毂部9的后侧面7侧以旋转中心线为中心环绕旋转轴线形成， 平面包括旋转轴的环形凹部的横截面被构造为椭圆形或卵形的主弧C的一部分，主弧C被形成为使得椭圆形状或形状被划分 通过长轴b作为椭圆形或对称形状的对称轴; 长轴b位于后侧表面7中。
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公开(公告)号：US09260971B2
公开(公告)日：2016-02-16
申请号：US13256151
申请日：2010-08-10
CPC分类号： F01D5/048 , F01D5/026 , F01D5/063 , F05D2230/232 , F05D2250/14 , F05D2250/293 , F05D2260/941
摘要： 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 part 9 connected to a rotor shaft 19 and a plurality of blade parts 11 formed around the outer periphery of the hub part 9, the hub part and the blade parts being integrated into one piece, wherein the diameter of the hub part 9 around the rotation axis L of the rotor shaft 19 gradually increases along the rotation axis direction toward a rear side surface 7 on an end side regarding the rotation axis direction; an annular recess 21 is formed annularly around the rotation axis as a rotation center line, on the side of the rear side surface 7 of the hub part 9; 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 7.
摘要翻译： 提供一种涡轮转子，其中可以在不改变叶片部分的几何形状的情况下减小涡轮转子的旋转惯性，而涡轮转子设置有后侧表面，使得在根部处出现的关于轮毂部分的应力集中 在后表面侧受到限制，以提高涡轮转子的强度和耐久性。 涡轮转子，其包括连接到转子轴19的毂部9和围绕毂部9的外周形成的多个叶片部11，轮毂部和叶片部一体地形成为一体，其中， 转子轴19的旋转轴线L周围的轮毂部9沿着旋转轴线方向朝向相对于旋转轴方向的端侧的后方侧面7逐渐增大; 环形凹部21在轮毂部9的后侧面7侧以旋转中心线为中心环绕旋转轴线形成， 平面包括旋转轴的环形凹部的横截面被构造为椭圆形或卵形的主弧C的一部分，主弧C被形成为使得椭圆形状或形状被划分 通过长轴b作为椭圆形或对称形状的对称轴; 长轴b位于后侧表面7中。
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公开(公告)号：US20130294895A1
公开(公告)日：2013-11-07
申请号：US13807258
申请日：2011-08-31
申请人： Takao Yokoyama , Hiroshi Suzuki , Motoki Ebisu , Toyotaka Yoshida
发明人： Takao Yokoyama , Hiroshi Suzuki , Motoki Ebisu , Toyotaka Yoshida
IPC分类号： F01D17/16
CPC分类号： F01D17/165 , F02B37/24 , F02C6/12 , F05D2220/40
摘要： A variable geometry turbine includes a fluid space formed by a nozzle mount and a nozzle plate; and a plurality of nozzle vanes arranged in the fluid space at certain intervals in the circumferential direction so as to partition the fluid space. The nozzle vanes are supported by shafts on the nozzle mount, in such a manner as to be capable of turning. The flow rate of the discharged fluid can be adjusted by opening or closing the cross-sectional area of a flow path formed by the adjacent nozzle vanes. The nozzle plate is provided with plate projections protruding toward the nozzle vanes further than, at least, end surfaces of the nozzle vanes, so as to cover the spaces between leading edges of the nozzle vanes and trailing edges of the nozzle vanes adjacent thereto, when the nozzle vanes are at a closed position.
摘要翻译： 可变几何涡轮机包括由喷嘴座和喷嘴板形成的流体空间; 以及沿圆周方向以一定间隔布置在流体空间中的多个喷嘴叶片，以便分隔流体空间。 喷嘴叶片以能够转动的方式由喷嘴座上的轴支撑。 可以通过打开或关闭由相邻喷嘴叶片形成的流路的横截面积来调节排出流体的流量。 喷嘴板设置有板突起，其比喷嘴叶片的至少端表面突出，以覆盖喷嘴叶片的前缘和与其相邻的喷嘴叶片的后缘之间的空间， 喷嘴叶片处于关闭位置。
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公开(公告)号：US09028202B2
公开(公告)日：2015-05-12
申请号：US13807258
申请日：2011-08-31
申请人： Takao Yokoyama , Hiroshi Suzuki , Motoki Ebisu , Toyotaka Yoshida
发明人： Takao Yokoyama , Hiroshi Suzuki , Motoki Ebisu , Toyotaka Yoshida
CPC分类号： F01D17/165 , F02B37/24 , F02C6/12 , F05D2220/40
摘要： A variable geometry turbine includes a fluid space formed by a nozzle mount and a nozzle plate; and a plurality of nozzle vanes arranged in the fluid space at certain intervals in the circumferential direction so as to partition the fluid space. The nozzle vanes are supported by shafts on the nozzle mount, in such a manner as to be capable of turning. The flow rate of the discharged fluid can be adjusted by opening or closing the cross-sectional area of a flow path formed by the adjacent nozzle vanes. The nozzle plate is provided with plate projections protruding toward the nozzle vanes further than, at least, end surfaces of the nozzle vanes, so as to cover the spaces between leading edges of the nozzle vanes and trailing edges of the nozzle vanes adjacent thereto, when the nozzle vanes are at a closed position.
摘要翻译： 可变几何涡轮机包括由喷嘴座和喷嘴板形成的流体空间; 以及沿圆周方向以一定间隔布置在流体空间中的多个喷嘴叶片，以便分隔流体空间。 喷嘴叶片以能够转动的方式由喷嘴座上的轴支撑。 可以通过打开或关闭由相邻喷嘴叶片形成的流路的横截面积来调节排出流体的流量。 喷嘴板设置有板突起，其比喷嘴叶片的至少端表面突出，以覆盖喷嘴叶片的前缘和与其相邻的喷嘴叶片的后缘之间的空间， 喷嘴叶片处于关闭位置。
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公开(公告)号：US09562442B2
公开(公告)日：2017-02-07
申请号：US13696235
申请日：2011-10-12
申请人： Toyotaka Yoshida , Motoki Ebisu
发明人： Toyotaka Yoshida , Motoki Ebisu
CPC分类号： F01D25/24 , F01D9/026 , F02B37/025 , F05D2220/40
摘要： In a turbine housing 12 of a turbocharger 10A of a twin-scroll type, a scroll-shaped passage is separated into a front scroll passage 42 and a rear scroll passage 44 by a partition wall 40. A front wall 50 and a root part 40b of the partition wall 40 curve toward a front side to secure cross-sectional areas a1, a2, a3 . . . and b1, b2, b3 . . . . The scroll passages 42, 44 are formed to have equal cross-sectional areas, a tip part 40a of the partition wall 40 is arranged perpendicular to the turbine rotor blade 26 and the scroll passages 42, 44 are symmetrical near the tip part 40a about an axis X so as to eliminate the flow rate difference.
摘要翻译： 在双涡旋型涡轮增压器10A的涡轮机壳体12中，涡旋状通路被分隔壁40分隔成前涡旋通道42和后涡旋通道44.前壁50和根部40b 分隔壁40向前侧弯曲以确保横截面区域a1，a2，a3。 。 。 和b1，b2，b3。 。 。 。 涡旋通道42,44形成为具有相等的横截面积，分隔壁40的末端部分40a垂直于涡轮转子叶片26设置，涡旋通道42,44围绕尖端部分40a对称 轴X，以消除流速差。
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公开(公告)号：US20130121820A1
公开(公告)日：2013-05-16
申请号：US13696235
申请日：2011-10-12
申请人： Toyotaka Yoshida , Motoki Ebisu
发明人： Toyotaka Yoshida , Motoki Ebisu
IPC分类号： F01D25/24
CPC分类号： F01D25/24 , F01D9/026 , F02B37/025 , F05D2220/40
摘要： In a turbine housing 12 of a turbocharger 10A of a twin-scroll type, a scroll-shaped passage is separated into a front scroll passage 42 and a rear scroll passage 44 by a partition wall 40. A front wall 50 and a root part 40b of the partition wall 40 curve toward a front side to secure cross-sectional areas a1, a2, a3 . . . and b1, b2, b3 . . . . The scroll passages 42, 44 are formed to have equal cross-sectional areas, a tip part 40a of the partition wall 40 is arranged perpendicular to the turbine rotor blade 26 and the scroll passages 42, 44 are symmetrical near the tip part 40a about an axis X so as to eliminate the flow rate difference.
摘要翻译： 在双涡旋型涡轮增压器10A的涡轮机壳体12中，涡旋状通路被分隔壁40分隔成前涡旋通道42和后涡旋通道44.前壁50和根部40b 分隔壁40向前侧弯曲以确保横截面区域a1，a2，a3。 。 。 和b1，b2，b3。 。 。 。 涡旋通道42,44形成为具有相等的横截面积，分隔壁40的末端部分40a垂直于涡轮转子叶片26设置，涡旋通道42,44围绕尖端部分40a对称 轴X，以消除流速差。
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