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1. 发明授权

US08985945B2 Radial gas expander 有权
标题翻译：径向气体膨胀机
公开(公告)号：US08985945B2
公开(公告)日：2015-03-24
申请号：US13266531
申请日：2010-07-28
申请人： Hideki Nagao , Yasushi Mori , Masahiro Kobayashi , Katsuya Yamashita , Hirotaka Higashimori , Katsuki Yagi
发明人： Hideki Nagao , Yasushi Mori , Masahiro Kobayashi , Katsuya Yamashita , Hirotaka Higashimori , Katsuki Yagi
IPC分类号： F01D5/04 , F01D1/08 , F02C7/06
CPC分类号： F01D1/08 , F01D5/04 , F02C7/06 , F05D2220/62
摘要： Provided is a uni-axial multi-stage radial gas expander which has a high degree of reliability and which can sufficiently cope with the conditions of a high pressure and a high pressure ratio. Two or more radial gas expander sections (11A, 11B) formed of two-or-more-stage impeller vanes (14a to 14h) arranged between bearings (21a, 21b) on a rotor shaft (13) consisting of a single shaft are housed in a signal casing (10).
摘要翻译：本发明提供一种具有高可靠性的单轴多级径向气体膨胀机，能够充分应对高压和高压比的条件。由设置在由单个轴组成的转子轴（13）上的轴承（21a，21b）之间的两级或更多级叶轮叶片（14a至14h）形成的两个或更多个径向气体膨胀器部分（11A，11B）在信号壳体（10）中。

2. 发明申请

US20120134797A1 MULTI-STAGE RADIAL TURBINE 审中-公开
标题翻译：多阶段径向涡轮机
公开(公告)号：US20120134797A1
公开(公告)日：2012-05-31
申请号：US13380247
申请日：2010-09-30
申请人： Hirotaka Higashimori , Katsuki Yagi
发明人： Hirotaka Higashimori , Katsuki Yagi
IPC分类号： F01D13/00 , F01D9/04
CPC分类号： F01D13/02 , F01D1/06 , F01D9/06 , F05D2210/43 , F05D2250/71
摘要： A multi-stage radial turbine that is capable of reducing the number of bearings and of improving the conversion efficiency is provided. Provided are a plurality of radial turbine rotor blades (5) that are attached at intervals to a single rotating shaft (3); a plurality of nozzles (19) that are individually installed on an upstream side of each of the radial turbine rotor blades and that accelerate a flow of fluid; a connecting channel portion (9) that connects gas an outlet portion (23) of the radial turbine rotor blade (5) on the front stage side and an upstream side of the nozzle (19) on the rear stage side, the connecting channel portion (9) being provided with a U-shaped bent portion (25) that deflects outward in the radial direction the flow of fluid that is made to flow out from the radial turbine rotor blade (5) in the shaft direction; a vane portion having a plurality of deflecting vanes (27) that deflect the flow of fluid inward in a rotation direction (R) while guiding the flow of fluid from the U-shaped bent portion (25) outward in the radial direction; and a return bent portion (31) that deflects inward in the radial direction the flow that is made to flow out from the vane portion (29) while swirling outward in the radial direction.
摘要翻译：提供能够减少轴承数量并提高转换效率的多级径向涡轮机。提供多个径向涡轮转子叶片（5），其间隔连接到单个旋转轴（3）; 多个喷嘴（19），其分别安装在每个径向涡轮转子叶片的上游侧并加速流体流动; 连接通道部分（9），其将气体连接到前级侧的径向涡轮转子叶片（5）的出口部分（23）和后级侧的喷嘴（19）的上游侧，连接通道部分（9）设置有U形弯曲部分（25），所述U形弯曲部分沿轴向向外偏转流体，所述流体流从径向涡轮转子叶片（5）沿轴向流出; 叶片部分具有多个偏转叶片（27），所述多个偏转叶片将流体沿旋转方向（R）向内偏转，同时沿着径向方向将流体从U形弯曲部分（25）向外引导; 以及在向径向向内偏转的同时在径向向外旋转的情况下使从叶片部（29）流出的流向偏转的返回弯曲部（31）。

3. 发明申请

US20120107108A1 RADIAL GAS EXPANDER 有权
标题翻译：径向气体膨胀机
公开(公告)号：US20120107108A1
公开(公告)日：2012-05-03
申请号：US13266531
申请日：2010-07-28
申请人： Hideki Nagao , Yasushi Mori , Masahiro Kobayashi , Katsuya Yamashita , Hirotaka Higashimori , Katsuki Yagi
发明人： Hideki Nagao , Yasushi Mori , Masahiro Kobayashi , Katsuya Yamashita , Hirotaka Higashimori , Katsuki Yagi
IPC分类号： F04D1/00
CPC分类号： F01D1/08 , F01D5/04 , F02C7/06 , F05D2220/62
摘要： Provided is a uni-axial multi-stage radial gas expander which has a high degree of reliability and which can sufficiently cope with the conditions of a high pressure and a high pressure ratio. Two or more radial gas expander sections (11A, 11B) formed of two-or-more-stage impeller vanes (14a to 14h) arranged between bearings (21a, 21b) on a rotor shaft (13) consisting of a single shaft are housed in a signal casing (10).
摘要翻译：本发明提供一种具有高可靠性的单轴多级径向气体膨胀机，能够充分应对高压和高压比的条件。由设置在由单个轴组成的转子轴（13）上的轴承（21a，21b）之间的两级或更多级叶轮叶片（14a至14h）形成的两个或更多个径向气体膨胀器部分（11A，11B）在信号壳体（10）中。

4. 发明授权

US07063508B2 Turbine rotor blade 有权
公开(公告)号：US07063508B2
公开(公告)日：2006-06-20
申请号：US10424729
申请日：2003-04-29
申请人： Hirotaka Higashimori , Katsuyuki Osako , Takashi Shiraishi , Takashi Mikogami
发明人： Hirotaka Higashimori , Katsuyuki Osako , Takashi Shiraishi , Takashi Mikogami
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/04 , F05D2220/40 , F05D2240/30 , F05D2250/71
摘要： A trailing edge of a turbine rotor blade is formed so that a deflection angle of a blade surface in a downstream side of a maximum blade thickness portion is a predetermined value or less, by forming the trailing edge of the rotor blade so as to be inclined from a center line of a blade thickness toward an extension line of a suction surface. Since the trailing edge of the rotor blade is thus formed, a rapid increase of the deflection angle is prevented in a trailing edge portion of the rotor blade. Accordingly, a rapid ascent portion and a rapid deceleration portion are not generated in a suction surface velocity in a main stream unlike the conventional case.

5. 发明申请

US20050163610A1 Diffuser for centrifugal compressor and method of producing the same 审中-公开
标题翻译：离心压缩机用扩散器及其制造方法
公开(公告)号：US20050163610A1
公开(公告)日：2005-07-28
申请号：US10503220
申请日：2003-12-04
申请人： Hirotaka Higashimori
发明人： Hirotaka Higashimori
IPC分类号： F04D29/44 , F01D1/02
CPC分类号： F04D29/444 , F05D2250/52
摘要： At least the throat of the suction surface of a conventionally-used diffuser blade having a two-dimensional shape is cut into a concave shape with a ball end mill. In the throat, the nearer to the bottom of the concave shape, the higher the gas pressure becomes, and therefore the gas flows from the concave bottom toward the hub end and the shroud end thereby to reduce the thickness of the boundary layer formed on the hub end and the shroud end.
摘要翻译：至少将具有二维形状的常规使用的扩散器叶片的吸入表面的喉部用球头铣刀切割成凹形。在喉部，更靠近凹形的底部，气体压力变得越高，因此气体从凹入的底部朝向轮毂端和护罩端部流动从而减小形成在其上的边界层的厚度轮毂端和护罩端。

6. 发明授权

US06877955B2 Mixed flow turbine and mixed flow turbine rotor blade 有权
标题翻译：混流式涡轮机和混流式涡轮机转子叶片
公开(公告)号：US06877955B2
公开(公告)日：2005-04-12
申请号：US10647340
申请日：2003-08-26
申请人： Hirotaka Higashimori , Takao Yokoyama , Takashi Mikogami , Shiro Yoshida
发明人： Hirotaka Higashimori , Takao Yokoyama , Takashi Mikogami , Shiro Yoshida
IPC分类号： F01D5/04 , F01D5/14 , F01O5/14
CPC分类号： F01D5/14
摘要： A mixed flow turbine includes a hub attached to a rotation axis and a plurality of rotor blades. Each of the plurality of rotor blades is attached to the hub in a radial direction, and the hub is rotated based on fluid supplied to a rotation region of the plurality of rotor blades. Each of the plurality of rotor blades has a curved shape that convexly swells on a supply side of the fluid.
摘要翻译：混合流动涡轮机包括附接到旋转轴线的毂和多个转子叶片。多个转子叶片中的每一个在径向方向上附接到轮毂，并且毂基于供应到多个转子叶片的旋转区域的流体而旋转。多个转子叶片中的每一个具有在流体的供给侧上凸起膨胀的弯曲形状。

7. 发明授权

US09500205B2 Multi-pressure radial turbine system 有权
标题翻译：多压径向涡轮系统
公开(公告)号：US09500205B2
公开(公告)日：2016-11-22
申请号：US14002468
申请日：2012-07-05
申请人： Hirotaka Higashimori , Norihiro Fukuda , Masayuki Kawami
发明人： Hirotaka Higashimori , Norihiro Fukuda , Masayuki Kawami
IPC分类号： F04D31/00 , F04D29/58 , F01K7/18 , F01D9/02 , F22B33/14 , F01K25/08
CPC分类号： F04D29/58 , F01D9/026 , F01K7/18 , F01K25/08 , F22B33/14
摘要： A multi-pressure radial turbine system including a high-pressure pump and a low-pressure pump for pressurizing liquid-phase heating media introduced therein to different pressures; a high-pressure evaporator and a low-pressure evaporator for vaporizing the liquid-phase heating media delivered from the high-pressure pump and the low-pressure pump by absorbing heat from a high-temperature heat source; one multi-pressure radial turbine that expands the gaseous heating media having different pressures and temperatures, supplied from the high-pressure evaporator and the low-pressure evaporator, to obtain output power; and a condenser for condensing the gaseous heating medium expanded in the multi-pressure radial turbine by making the medium release heat to a low-pressure heat source. A cycle circuit is formed through which the heating medium circulates while repeatedly changing its state between vapor and liquid.
摘要翻译：一种多压力径向涡轮机系统，包括高压泵和低压泵，用于将引入其中的液相加热介质加压到不同的压力; 用于通过从高温热源吸收热量来蒸发从高压泵和低压泵输送的液相加热介质的高压蒸发器和低压蒸发器; 一个多压力径向涡轮，其膨胀由高压蒸发器和低压蒸发器供应的具有不同压力和温度的气态加热介质，以获得输出功率; 以及冷凝器，用于通过使介质向低压热源释放热量来冷凝在多压径向涡轮机中膨胀的气态加热介质。形成一循环回路，加热介质通过该循环循环，同时重复地改变其在蒸气和液体之间的状态。

8. 发明申请

US20100143095A1 RADIAL COMPRESSOR 有权
标题翻译：径向压缩机
公开(公告)号：US20100143095A1
公开(公告)日：2010-06-10
申请号：US12665229
申请日：2009-02-19
申请人： Hirotaka Higashimori , Koichi Sugimoto , Hideyoshi Isobe , Takashi Shiraishi
发明人： Hirotaka Higashimori , Koichi Sugimoto , Hideyoshi Isobe , Takashi Shiraishi
IPC分类号： F04D27/02 , F04D29/42
CPC分类号： F04D29/441 , F04D29/4213 , F04D29/685 , F05D2220/40 , F05D2250/51
摘要： A radial compressor is capable of preventing the occurrence of separation caused by a flow which goes beyond the front end of a blade and turns onto a negative pressure plane from a pressure plane, thereby reducing a surging flow rate to a smaller flow rate. The radial compressor includes an impeller which is rotatively driven, axially introduces air taken in through an air inlet passage formed in a housing, pressurizes the introduced air, and discharges the pressurized air in a radial direction, wherein an annular concave groove is formed in a peripheral wall of the air inlet passage of the housing, a rear end portion of an opening of the annular concave groove, which rear end portion meets the housing peripheral wall, is provided in the vicinity of a blade front end surface of the impeller, and the rear end portion of the opening of the annular concave groove is formed such that an axial projecting amount X thereof relative to the blade front end surface of the impeller is set to −1T≦X≦1.5T (where T denotes the thickness of the distal portion of a blade).
摘要翻译：径向压缩机能够防止由超过叶片前端的流动引起的分离发生，并从压力平面转到负压平面，从而将浪涌流量减小到较小的流量。径向压缩机包括旋转驱动的叶轮，轴向地引入通过形成在壳体中的空气入口通道吸入的空气，对引入的空气加压，并且沿径向排出加压空气，其中环形凹槽形成在壳体的进气通道的周壁，后端部与壳体周壁相接触的环形凹槽的开口的后端部设置在叶轮的叶片前端面附近，环形凹槽的开口的后端部形成为使得其相对于叶轮的叶片前端面的轴向突出量X被设定为-1T＆lt; NlE; X＆lt; llE; 1.5T（其中T表示叶片的远端部分）。

9. 发明申请

US20100129209A1 Centrifugal Compressor 审中-公开
标题翻译：离心式压缩机
公开(公告)号：US20100129209A1
公开(公告)日：2010-05-27
申请号：US11989241
申请日：2007-02-09
申请人： Koichi Sugimoto , Takashi Shiraishi , Hirotaka Higashimori , Hideyoshi Isobe
发明人： Koichi Sugimoto , Takashi Shiraishi , Hirotaka Higashimori , Hideyoshi Isobe
IPC分类号： F04D29/44
CPC分类号： F04D29/441
摘要： There is provided a centrifugal compressor having a diffuser structure in which airflow is unlikely to separate from a hub side wall surface on a hub side wall surface downstream side within a diffuser passage. In a centrifugal compressor provided with a diffuser passage 15 for recovering static pressure by slowing down discharged air from an outer circumferential end of an impeller that rotates within a housing 11, a hub side wall surface 15b of the diffuser passage 15 is provided with an inclined plane 20 that approaches toward a shroud side, in a position on a downstream side of a portion parallel with a normal line direction of a section surface of an impeller exit.
摘要翻译：提供了一种具有扩散器结构的离心式压缩机，其中气流不可能与扩散器通道内的轮毂侧壁表面下游侧上的轮毂侧壁表面分离。在设置有扩散通路15的离心式压缩机中，通过使从外壳11内旋转的叶轮的外周端减速排出的空气来回收静压，扩散通路15的毂侧壁面15b设有倾斜在与叶轮出口的截面的法线方向平行的部分的下游侧的位置处朝向护罩侧的平面20。

10. 发明申请

US20150218949A1 MIXED FLOW TURBINE 有权
标题翻译：混合流量涡轮机
公开(公告)号：US20150218949A1
公开(公告)日：2015-08-06
申请号：US14359140
申请日：2012-09-06
申请人： Hirotaka Higashimori
发明人： Hirotaka Higashimori
IPC分类号： F01D5/04 , F01D1/02
CPC分类号： F01D5/048 , F01D1/026 , F01D5/141 , F01D9/026 , F05D2210/43 , F05D2220/40 , F05D2240/241
摘要： An object is to provide a mixed flow turbine, wherein intermediate blades having an intermediate height are provided between main blades of the mixed flow turbine, thus improving an impulse blade turbine characteristic and reducing the moment of inertia for a rotor blade as a whole, thereby improving the efficiency and transient response. The mixed flow turbine includes: a turbine rotor blade 11; a turbine housing 3; a scroll partition wall 17 dividing a scroll chamber 13; a shroud-side inflow passageway 35 formed on the side of a shroud-side partition wall surface 25; and a hub-side inflow passageway 29 formed on the side of a hub-side partition wall surface 23, wherein the rotor blade 11 includes: main blades 37 formed with a height spanning the entire extent between a hub outer circumferential surface 31 and the inner periphery surface of a shroud portion 15; and intermediate blades 39 arranged in the circumferential direction between the main blades 37 and arranged so as to extend from the inlet portion of the main blades 37 to an intermediate portion and having an intermediate height with respect to the height of the main blades 37, wherein a fluid from the hub-side inflow passageway 29 flows in through front edges of the intermediate blades 39.
摘要翻译：目的是提供一种混合流动涡轮机，其中具有中间高度的中间叶片设置在混合流动涡轮机的主叶片之间，从而改善了脉冲叶片涡轮机特性并减小了整体上转子叶片的惯性矩，从而提高效率和瞬态响应。混合流动涡轮机包括：涡轮机转子叶片11; 涡轮机壳体3; 分隔涡旋室13的涡旋分隔壁17; 形成在护罩侧隔壁表面25侧的护罩侧流入通道35; 以及形成在轮毂侧分隔壁面23侧的轮毂侧流入通路29，其中，转子叶片11包括：主叶片37，其形成为跨越轮毂外周面31和内侧护罩部分15的周边表面; 以及在主叶片37之间沿圆周方向布置的中间叶片39，其布置成从主叶片37的入口部分延伸到中间部分，并且具有相对于主叶片37的高度的中间高度，其中来自轮毂侧流入通道29的流体流入中间叶片39的前缘。

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