公开(公告)号：US20100275616A1

公开(公告)日：2010-11-04

申请号：US12743545

申请日：2008-11-05

申请人： Nobuyoshi Saji ,  Toshio Takahashi ,  Seiichiro Yoshinaga ,  Hirohisa Wakisaka

发明人： Nobuyoshi Saji ,  Toshio Takahashi ,  Seiichiro Yoshinaga ,  Hirohisa Wakisaka

IPC分类号： F25B9/00

CPC分类号： F25B9/14 ,  F25B9/06 ,  F25B45/00 ,  F25B2309/1401 ,  F25B2400/16 ,  F25B2500/27 ,  F25B2600/2519 ,  F25J1/005 ,  F25J1/0062 ,  F25J1/0065 ,  F25J1/0248 ,  F25J2245/02 ,  F25J2270/16 ,  F25J2270/912

摘要： A cryogenic refrigerator (10) which generates a cryogenic temperature by compressing and expanding a working gas in a closed loop (11). The cryogenic refrigerator comprises a bypass line (22) allowing a high-pressure portion and a low-pressure portion to communicate with each other, a gas storage tank (24) located midway in the bypass line and having pressure regulation valves (23a, 23b) on the high-pressure side and the low-pressure side, respectively, and a pressure control unit (26) controlling the pressure regulation valves. The pressure control unit (26) controls the pressure regulation valves (23a, 23b) so that the pressure in the gas storage tank (24) is equal to the pressure in the closed loop at room temperature and in a stopped state and so that the pressure in the gas storage tank (24) is between the pressures in the high-pressure portion and in the low-pressure portion and is close to the pressure in the low-pressure portion in an operating state.

摘要翻译： 一种低温冰箱（10），其通过在闭环（11）中压缩和膨胀工作气体而产生低温温度。 低温冷冻机包括允许高压部分和低压部分彼此连通的旁通管线（22），位于旁路管线中间的储气罐（24），并具有压力调节阀（23a，23b ）和控制压力调节阀的压力控制单元（26）分别设置在高压侧和低压侧。 压力控制单元（26）控制压力调节阀（23a，23b），使得气体储存箱（24）中的压力等于在室温和停止状态下的闭环中的压力， 气体储罐（24）中的压力处于高压部分和低压部分的压力之间，并且在操作状态下接近低压部分的压力。

公开(公告)号：US08113769B2

公开(公告)日：2012-02-14

申请号：US12058901

申请日：2008-03-31

申请人： Toshio Takahashi ,  Seiichiro Yoshinaga ,  Hirohisa Wakisaka

发明人： Toshio Takahashi ,  Seiichiro Yoshinaga ,  Hirohisa Wakisaka

IPC分类号： F01D17/12

CPC分类号： F02C1/02 ,  F01D15/005 ,  F01D17/165 ,  F05D2220/76 ,  F25B9/06

摘要： Expansion turbine having a variable nozzle mechanism comprises an adiabatic expansion device located in a vacuum container having a turbine impeller therein which rotates and drives the turbine impeller during adiabatic expansion of very low temperature gas, and varies the throat area of very low temperature gas introduced in the turbine impeller by driving a nozzle member disposed near the outside end of the adiabatic expansion device by a drive force from a driving member located outside the vacuum container; a plate member provided detachably in contact with the outside end of the body of the adiabatic expansion device, wherein the support side of the nozzle member is connected to and supported by the plate member, and the drive side of the nozzle member is connected to and supported by the driving member.

摘要翻译： 具有可变喷嘴机构的膨胀涡轮机包括位于真空容器中的绝热膨胀装置，其中具有涡轮机叶轮，其中在非常低温的气体的绝热膨胀期间旋转并驱动涡轮叶轮，并且改变引入的极低温气体的喉部面积 所述涡轮叶轮通过驱动来自位于所述真空容器外部的驱动构件的驱动力驱动设置在所述绝热膨胀装置的外端附近的喷嘴构件; 与绝热膨胀装置的本体的外端可拆卸地设置的板构件，其中，所述喷嘴构件的支撑侧连接并由所述板构件支撑，并且所述喷嘴构件的驱动侧与 由驾驶员支持。

公开(公告)号：US20090028693A1

公开(公告)日：2009-01-29

申请号：US12054880

申请日：2008-03-25

申请人： Toshio Takahashi ,  Seiichiro Yoshinaga ,  Hirohisa Wakisaka

发明人： Toshio Takahashi ,  Seiichiro Yoshinaga ,  Hirohisa Wakisaka

IPC分类号： F01D15/00 ,  F01D25/12

CPC分类号： F01D15/00 ,  F05D2260/903 ,  H02K49/043

摘要： A braking mechanism is provided that is suitable for an expansion turbine that rotates at high speed. Upper end salient poles 26a and 26b are formed in two opposite places on the outer peripheral upper end of a rotating shaft 12, and lower end salient poles 28a and 28b are formed in two opposite places on the outer peripheral lower end of the rotating shaft 12 such that they are staggered in the vertical direction with respect to the upper end salient poles 26a and 26b. A casing 22 is provided in a location facing an outer periphery of the rotating shaft 12, and an excitation coil 30 is provided on the casing 22 for forming a magnetic path between the upper end salient poles 26a and 26b and the lower end salient poles 28a and 28b. By rotation of the rotating shaft 12, and by the magnetic path formed by the excitation coil 30, eddy currents are generated in the casing 22.

摘要翻译： 提供了适用于高速旋转的膨胀涡轮的制动机构。 上端凸极26a和26b形成在旋转轴12的外周上端的两个相对位置，下端凸极28a和28b形成在旋转轴12的外周下端的两个相对位置 使得它们相对于上端凸极26a和26b在垂直方向上交错。 在面向旋转轴12的外周的位置设置有壳体22，在壳体22上设置有用于在上端凸极26a和26b与下端凸极28a之间形成磁路的励磁线圈30 和28b。 通过旋转轴12的旋转以及由励磁线圈30形成的磁路，在壳体22内产生涡电流。

公开(公告)号：US08262350B2

公开(公告)日：2012-09-11

申请号：US12054916

申请日：2008-03-25

申请人： Seiichiro Yoshinaga ,  Toshio Takahashi ,  Hirohisa Wakisaka

发明人： Seiichiro Yoshinaga ,  Toshio Takahashi ,  Hirohisa Wakisaka

IPC分类号： F01D5/08 ,  F04D29/58

CPC分类号： F01D15/005 ,  F01D25/145 ,  F05D2230/233 ,  F05D2260/903 ,  Y10T29/49236

摘要： A heat insulating structure for an expansion turbine includes an adiabatic expansion device including an expander body that includes an outlet passage for refrigerant fluid at a central portion thereof and an introduction chamber for refrigerant fluid communicating with an inlet of the outlet passage on an outer peripheral portion thereof, and a turbine impeller that is rotatably provided at the inlet and braked by a braking device. The adiabatic expansion device adiabatically expands refrigerant fluid by rotating the turbine impeller with refrigerant fluid that flows from the introduction chamber to the outlet passage side. A heat-insulating layer, which surrounds the entire periphery of the outlet passage over the entire length of the introduction chamber, is formed between the introduction chamber and the outlet passage. Accordingly, it is possible to improve turbine efficiency by reducing transfer of heat of refrigerant fluid from the introduction chamber to the outlet passage.

摘要翻译： 用于膨胀涡轮机的绝热结构包括绝热膨胀装置，该绝热膨胀装置包括膨胀机体，该膨胀机主体包括在其中心部分处的用于制冷剂流体的出口通道和用于在外周部分与出口通道的入口连通的制冷剂流体导入室 以及可旋转地设置在入口处并由制动装置制动的涡轮叶轮。 绝热膨胀装置通过从引入室流向出口通道侧的制冷剂流体旋转涡轮叶轮，绝热地膨胀制冷剂流体。 在引入室和出口通道之间形成有在引入室的整个长度上围绕出口通道的整个周边的绝热层。 因此，可以通过减少制冷剂流体从引入室向出口通道的转移而提高涡轮效率。

公开(公告)号：US08231339B2

公开(公告)日：2012-07-31

申请号：US12057616

申请日：2008-03-28

申请人： Seiichiro Yoshinaga ,  Toshio Takahashi ,  Hirohisa Wakisaka

发明人： Seiichiro Yoshinaga ,  Toshio Takahashi ,  Hirohisa Wakisaka

IPC分类号： F04D29/44

CPC分类号： F01D15/005 ,  F01D17/165

摘要： Expansion turbine having a variable nozzle mechanism comprises an adiabatic expansion device located in a vacuum container having a turbine impeller therein which rotates and drives the turbine impeller during adiabatic expansion of very low temperature gas, and varies the throat area of very low temperature gas introduced in the turbine impeller by driving a nozzle member disposed near the outside end of the adiabatic expansion device by a drive force from a driving member located outside the vacuum container; wherein the driving member comprises a cylindrical member disposed coaxially with the turbine impeller, and the nozzle member is provided on the extension of the body of the cylindrical member in the axial direction.

摘要翻译： 具有可变喷嘴机构的膨胀涡轮机包括位于真空容器中的绝热膨胀装置，其中具有涡轮机叶轮，其中在非常低温的气体的绝热膨胀期间旋转并驱动涡轮叶轮，并且改变引入的极低温气体的喉部面积 所述涡轮叶轮通过驱动来自位于所述真空容器外部的驱动构件的驱动力驱动设置在所述绝热膨胀装置的外端附近的喷嘴构件; 其特征在于，所述驱动部件具有与所述涡轮叶轮同轴配置的筒状部件，所述喷嘴部件沿所述轴向设置在所述筒状体的主体的延伸部上。

公开(公告)号：US20080240911A1

公开(公告)日：2008-10-02

申请号：US12054916

申请日：2008-03-25

申请人： Seiichiro Yoshinaga ,  Toshio Takahashi ,  Hirohisa Wakisaka

发明人： Seiichiro Yoshinaga ,  Toshio Takahashi ,  Hirohisa Wakisaka

IPC分类号： F01D25/08 ,  B23P15/26

CPC分类号： F01D15/005 ,  F01D25/145 ,  F05D2230/233 ,  F05D2260/903 ,  Y10T29/49236

摘要： A heat insulating structure for an expansion turbine includes an adiabatic expansion device including an expander body that includes an outlet passage for refrigerant fluid at a central portion thereof and an introduction chamber for refrigerant fluid communicating with an inlet of the outlet passage on an outer peripheral portion thereof, and a turbine impeller that is rotatably provided at the inlet and braked by a braking device. The adiabatic expansion device adiabatically expands refrigerant fluid by rotating the turbine impeller with refrigerant fluid that flows from the introduction chamber to the outlet passage side. A heat-insulating layer, which surrounds the entire periphery of the outlet passage over the entire length of the introduction chamber, is formed between the introduction chamber and the outlet passage. Accordingly, it is possible to improve turbine efficiency by reducing transfer of heat of refrigerant fluid from the introduction chamber to the outlet passage.

摘要翻译： 用于膨胀涡轮机的绝热结构包括绝热膨胀装置，该绝热膨胀装置包括膨胀机体，该膨胀机主体包括在其中心部分处的用于制冷剂流体的出口通道和用于在外周部分与出口通道的入口连通的制冷剂流体导入室 以及可旋转地设置在入口处并由制动装置制动的涡轮叶轮。 绝热膨胀装置通过从引入室流向出口通道侧的制冷剂流体旋转涡轮叶轮，绝热地膨胀制冷剂流体。 在引入室和出口通道之间形成有在引入室的整个长度上围绕出口通道的整个周边的绝热层。 因此，可以通过减少制冷剂流体从引入室向出口通道的转移而提高涡轮效率。

公开(公告)号：US08257026B2

公开(公告)日：2012-09-04

申请号：US12054880

申请日：2008-03-25

申请人： Toshio Takahashi ,  Seiichiro Yoshinaga ,  Hirohisa Wakisaka

发明人： Toshio Takahashi ,  Seiichiro Yoshinaga ,  Hirohisa Wakisaka

IPC分类号： F01D15/12 ,  F01D25/12

CPC分类号： F01D15/00 ,  F05D2260/903 ,  H02K49/043

摘要： A braking mechanism is provided that is suitable for an expansion turbine that rotates at high speed. Upper end salient poles 26a and 26b are formed in two opposite places on the outer peripheral upper end of a rotating shaft 12, and lower end salient poles 28a and 28b are formed in two opposite places on the outer peripheral lower end of the rotating shaft 12 such that they are staggered in the vertical direction with respect to the upper end salient poles 26a and 26b. A casing 22 is provided in a location facing an outer periphery of the rotating shaft 12, and an excitation coil 30 is provided on the casing 22 for forming a magnetic path between the upper end salient poles 26a and 26b and the lower end salient poles 28a and 28b. By rotation of the rotating shaft 12, and by the magnetic path formed by the excitation coil 30, eddy currents are generated in the casing 22.

摘要翻译： 提供了适用于高速旋转的膨胀涡轮的制动机构。 上端凸极26a和26b形成在旋转轴12的外周上端的两个相对位置，下端凸极28a和28b形成在旋转轴12的外周下端的两个相对位置 使得它们相对于上端凸极26a和26b在垂直方向上交错。 在面向旋转轴12的外周的位置设置有壳体22，在壳体22上设置有用于在上端凸极26a和26b与下端凸极28a之间形成磁路的励磁线圈30 和28b。 通过旋转轴12的旋转以及由励磁线圈30形成的磁路，在壳体22内产生涡电流。

公开(公告)号：US06382910B1

公开(公告)日：2002-05-07

申请号：US09695905

申请日：2000-10-26

申请人： Takashi Kato ,  Katsumi Kawano ,  Toru Shimba ,  Tadao Hiyama ,  Hiroshi Tsuji ,  Seiichiro Yoshinaga ,  Hiroshi Asakura ,  Nobuyoshi Saji ,  Takehiko Ishizawa

发明人： Takashi Kato ,  Katsumi Kawano ,  Toru Shimba ,  Tadao Hiyama ,  Hiroshi Tsuji ,  Seiichiro Yoshinaga ,  Hiroshi Asakura ,  Nobuyoshi Saji ,  Takehiko Ishizawa

IPC分类号： F01D1712

CPC分类号： F01D17/165 ,  Y10S62/91

摘要： An adiabatic expansion apparatus 22 with a built-in turbine impeller 12 adiabatically expands gas at a cryogenic temperature when the impeller rotates. A control device 24 is connected coaxially with the turbine impeller to control the impeller. A variable nozzle mechanism 30 is provided for varying the throat area for the gas at a cryogenic temperature to be introduced into the turbine impeller. The adiabatic expansion apparatus is installed in a vacuum vessel 14, and a control device is disposed outside the vacuum vessel. The variable nozzle mechanism comprises a nozzle component 32 built into the adiabatic expansion apparatus, and a driving component 34 installed outside the vacuum vessel. The nozzle component and the driving component are connected to the turbine impeller with a coaxial, thin cylindrical component 36, and drive the nozzle component when the cylindrical component rotates about the axis Z of the turbine impeller. The actuator and most of components of the nozzle driving mechanism can be installed at normal temperature under atmospheric pressure, the heat input can be suppressed to an extremely minimal level, and the variable nozzle of the expansion turbine can be driven. Thus, according to the invention, helium gas at a cryogenic temperature can be expanded adiabatically at a high adiabatic efficiency.

摘要翻译： 具有内置涡轮叶轮12的绝热膨胀装置22在叶轮旋转时在低温下绝热膨胀气体。 控制装置24与涡轮机叶轮同轴地连接以控制叶轮。 提供可变喷嘴机构30，用于改变在低温下气体的喉部区域，以引入涡轮叶轮。 绝热膨胀装置安装在真空容器14中，控制装置设置在真空容器的外部。 可变喷嘴机构包括内置于绝热膨胀装置中的喷嘴部件32和安装在真空容器外部的驱动部件34。 喷嘴部件和驱动部件通过同轴的薄的圆柱形部件36连接到涡轮机叶轮，并且当圆柱形部件围绕涡轮叶轮的轴线Z旋转时驱动喷嘴部件。 致动器和喷嘴驱动机构的大部分部件可以在大气压下的常温下进行安装，能够将热输入抑制到极小的水平，并且可以驱动膨胀涡轮机的可变喷嘴。 因此，根据本发明，在低温下的氦气可以以绝热的高效绝热膨胀。