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1. 发明授权

US09777578B2 Radial turbine blade 有权
公开(公告)号：US09777578B2
公开(公告)日：2017-10-03
申请号：US14655296
申请日：2012-12-27
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Takao Yokoyama , Masaki Tojo , Satomi Nagae
IPC分类号： F01D5/14 , F01D25/24 , F01D5/04 , F01D1/22 , F02C6/12 , F02B37/24
CPC分类号： F01D5/14 , F01D1/22 , F01D5/04 , F01D5/141 , F01D25/24 , F02B37/24 , F02C6/12 , F05D2220/30 , F05D2240/301
摘要： An object is to provide a radial turbine blade that can reduce an impact loss of inflowing gas at a leading edge of the turbine blade and achieve a higher turbine efficiency, even in a case of a flow field corresponding to a low turbine operational velocity ratio U/C0 due to a throttling operation on a variable nozzle mechanism of a variable geometry turbocharger.In a radial turbine blade, a hub-side end portion Pa at a leading edge 51 of a turbine blade 50 is formed to be positioned more on a rear side in a rotation direction R of the turbine blade 50 than a shroud-side end portion Sc at the leading edge 51, and a straight line connecting between the shroud-side end portion Sc and the hub-side end portion Pa is inclined with respect to a straight line extending in a rotation axis direction from the shroud-side end portion Sc at the leading edge 51 onto a hub 17 surface by an angle in a range from 30° to 70° as viewed in the radial direction of the turbine blade 50.

2. 发明申请

US20150104296A1 VARIABLE GEOMETRY TURBOCHARGER 有权
标题翻译：可变几何涡轮机
公开(公告)号：US20150104296A1
公开(公告)日：2015-04-16
申请号：US14381237
申请日：2013-02-26
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Takao Yokoyama , Katsuyuki Osako , Isao Tomita , Yasuaki Jinnai , Masaki Tojo , Satomi Nagae
IPC分类号： F04D27/00 , F02B37/22
CPC分类号： F04D27/002 , F01D5/141 , F01D17/16 , F01D17/165 , F02B37/22 , F02B37/24 , F02C6/12 , F05D2220/40 , F05D2250/712 , F05D2250/713 , F05D2250/75 , Y02T10/144
摘要： 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 vanes 41a disposed at predetermined intervals around a rotational shaft center of a turbine wheel 7 so as to surround an outer circumferential side of the turbine wheel 7 and a variable nozzle mechanism configured capable of changing a blade angle of each of the nozzle vanes 41a, each of the nozzle vanes 41a having a blade cross-section orthogonal to a nozzle shaft 41b of each nozzle vane 41a, the blade cross-section having: a concave portion 53 curved into a concave shape on at least a part of a pressure surface 45 side, the part being disposed at a trailing edge 51 side with respect to the rotational center C; and a convex portion at a leading edge 49 side with respect to the rotational center C, so that a surface shape of the pressure surface 45 side 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.
摘要翻译：在包括可变喷嘴机构的可变几何涡轮增压器中，目的是增强可变喷嘴机构的故障时的安全性，并且通过施加作用在喷嘴叶片上的力矩来提高可变喷嘴机构的控制精度打开方向牢固稳定。可变几何涡轮增压器包括多个喷嘴叶片41a，其围绕涡轮机叶轮7的外周侧围绕涡轮机叶轮7的旋转轴中心以预定间隔设置，并且可变喷嘴机构构造成能够改变叶片角度每个喷嘴叶片41a，每个喷嘴叶片41a具有与每个喷嘴叶片41a的喷嘴轴41b正交的叶片横截面，叶片横截面具有：在其上弯曲成凹形的凹部53 至少一部分压力表面45侧，该部分相对于旋转中心C设置在后缘51侧; 以及相对于旋转中心C的前缘49侧的凸部，使得压力面45侧的表面形状为大致S字状，在相同的纵向上具有跨越边界的凹部和凸部位置作为旋转中心。

3. 发明授权

US09926938B2 Variable geometry turbocharger 有权
公开(公告)号：US09926938B2
公开(公告)日：2018-03-27
申请号：US14381237
申请日：2013-02-26
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Takao Yokoyama , Katsuyuki Osako , Isao Tomita , Yasuaki Jinnai , Masaki Tojo , Satomi Nagae
IPC分类号： F04D27/00 , F02B37/24 , F01D17/16 , F01D5/14 , F02B37/22 , F02C6/12
CPC分类号： F04D27/002 , F01D5/141 , F01D17/16 , F01D17/165 , F02B37/22 , F02B37/24 , F02C6/12 , F05D2220/40 , F05D2250/712 , F05D2250/713 , F05D2250/75 , Y02T10/144
摘要： 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 vanes 41a disposed at predetermined intervals around a rotational shaft center of a turbine wheel 7 so as to surround an outer circumferential side of the turbine wheel 7 and a variable nozzle mechanism configured capable of changing a blade angle of each of the nozzle vanes 41a, each of the nozzle vanes 41a having a blade cross-section orthogonal to a nozzle shaft 41b of each nozzle vane 41a, the blade cross-section having: a concave portion 53 curved into a concave shape on at least a part of a pressure surface 45 side, the part being disposed at a trailing edge 51 side with respect to the rotational center C; and a convex portion at a leading edge 49 side with respect to the rotational center C, so that a surface shape of the pressure surface 45 side 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.

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