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    Impingement cooled structure
    1.
    发明授权
    Impingement cooled structure 有权
    冲击冷却结构

    公开(公告)号：US08137056B2

    公开(公告)日：2012-03-20

    申请号：US12281369

    申请日：2007-02-26

    申请人： Shu Fujimoto ,  Youji Ohkita ,  Yoshitaka Fukuyama ,  Takashi Yamane ,  Masahiro Matsushita ,  Toyoaki Yoshida

    发明人： Shu Fujimoto ,  Youji Ohkita ,  Yoshitaka Fukuyama ,  Takashi Yamane ,  Masahiro Matsushita ,  Toyoaki Yoshida

    IPC分类号： F04D31/00

    CPC分类号： F01D25/246 ,  F01D11/08 ,  F01D11/24 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2214

    摘要： An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto.

    摘要翻译： 冲击冷却结构包括沿圆周方向设置的多个护罩构件，以构成围绕热气流的环形罩，以及安装在护罩构件的径向外表面上以在其间形成空腔的罩盖。 护罩盖具有与空腔连通的第一冲击冷却孔，并允许将冷却空气喷射到其内部，以便通过冲击来冷却腔的内表面。 护罩构件各自具有孔翅片。 孔鳍将空腔分成多个子腔。 此外，孔翅片具有第二冲击冷却孔，其允许流过第一冲击冷却孔的冷却空气倾斜地朝与其相邻的子腔的底表面喷射。

    IMPINGEMENT COOLED STRUCTURE
    2.
    发明申请
    IMPINGEMENT COOLED STRUCTURE 有权
    冲击冷却结构

    公开(公告)号：US20090035125A1

    公开(公告)日：2009-02-05

    申请号：US12281369

    申请日：2007-02-26

    申请人： Shu Fujimoto ,  Youji Ohkita ,  Yoshitaka Fukuyama ,  Takashi Yamane ,  Masahiro Matsushita ,  Toyoaki Yoshida

    发明人： Shu Fujimoto ,  Youji Ohkita ,  Yoshitaka Fukuyama ,  Takashi Yamane ,  Masahiro Matsushita ,  Toyoaki Yoshida

    IPC分类号： F01D25/12 ,  F02C7/18

    CPC分类号： F01D25/246 ,  F01D11/08 ,  F01D11/24 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2214

    摘要： An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto.

    摘要翻译： 冲击冷却结构包括沿圆周方向设置的多个护罩构件，以构成围绕热气流的环形罩，以及安装在护罩构件的径向外表面上以在其间形成空腔的罩盖。 护罩盖具有与空腔连通的第一冲击冷却孔，并允许将冷却空气喷射到其内部，以便通过冲击来冷却腔的内表面。 护罩构件各自具有孔翅片。 孔鳍将空腔分成多个子腔。 此外，孔翅片具有第二冲击冷却孔，其允许流过第一冲击冷却孔的冷却空气倾斜地朝与其相邻的子腔的底表面喷射。

    Cooling structure of turbine airfoil
    5.
    发明授权
    Cooling structure of turbine airfoil 有权
    涡轮机翼的冷却结构

    公开(公告)号：US09133717B2

    公开(公告)日：2015-09-15

    申请号：US12812227

    申请日：2009-01-08

    申请人： Chiyuki Nakamata ,  Takashi Yamane ,  Yoshitaka Fukuyama ,  Takahiro Bamba

    发明人： Chiyuki Nakamata ,  Takashi Yamane ,  Yoshitaka Fukuyama ,  Takahiro Bamba

    IPC分类号： F01D5/18

    CPC分类号： F01D5/189 ,  F01D5/186 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

    摘要： A cooling structure of a turbine airfoil cools a turbine airfoil (10) exposed to hot gas (1), using cooling air (2) of a temperature lower than that of the hot gas. The turbine airfoil (10) includes an external surface (11), an internal surface (12) opposite to the external surface, a plurality of film-cooling holes (13) blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections (14) integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert (20) which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes (21) for impingement-cooling the internal surface (12).

    摘要翻译： 涡轮翼型件的冷却结构使用比热气体的温度低的冷却空气（2）冷却暴露于热气体（1）的涡轮机翼型件（10）。 涡轮机翼（10）包括外表面（11），与外表面相对的内表面（12），多个薄膜冷却孔（13），其将冷却空气从内表面向外表面吹向薄膜 - 冷却外表面，以及多个传热促进突起（14），其与内表面整体形成并从内表面向内突出。 涡轮机翼片还包括中空圆柱形插入件（20），该中空圆柱形插入件位于涡轮机翼片的内表面内部，并且供应冷却空气。 插入件具有用于冲击冷却内表面（12）的多个冲击孔（21）。

    COOLING STRUCTURE OF TURBINE AIRFOIL
    6.
    发明申请
    COOLING STRUCTURE OF TURBINE AIRFOIL 有权
    涡轮机空气冷却结构

    公开(公告)号：US20110027102A1

    公开(公告)日：2011-02-03

    申请号：US12812227

    申请日：2009-01-08

    申请人： Chiyuki Nakamata ,  Takashi Yamane ,  Yoshitaka Fukuyama ,  Takahiro Bamba

    发明人： Chiyuki Nakamata ,  Takashi Yamane ,  Yoshitaka Fukuyama ,  Takahiro Bamba

    IPC分类号： F01D5/18

    CPC分类号： F01D5/189 ,  F01D5/186 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

    摘要： A cooling structure of a turbine airfoil cools a turbine airfoil (10) exposed to hot gas (1), using cooling air (2) of a temperature lower than that of the hot gas. The turbine airfoil (10) includes an external surface (11), an internal surface (12) opposite to the external surface, a plurality of film-cooling holes (13) blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections (14) integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert (20) which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes (21) for impingement-cooling the internal surface (12).

    摘要翻译： 涡轮翼型件的冷却结构使用比热气体的温度低的冷却空气（2）冷却暴露于热气体（1）的涡轮机翼型件（10）。 涡轮机翼（10）包括外表面（11），与外表面相对的内表面（12），多个薄膜冷却孔（13），其将冷却空气从内表面向外表面吹向薄膜 - 冷却外表面，以及多个传热促进突起（14），其与内表面整体形成并从内表面向内突出。 涡轮机翼片还包括中空圆柱形插入件（20），该中空圆柱形插入件位于涡轮机翼片的内表面内部，并且供应冷却空气。 插入件具有用于冲击冷却内表面（12）的多个冲击孔（21）。

    Extracorperal ultrasonic irradition of titanium oxide (TiO2) coated implant for angiogenesis stimulation
    7.
    发明授权
    Extracorperal ultrasonic irradition of titanium oxide (TiO2) coated implant for angiogenesis stimulation 有权
    氧化钛（TiO2）涂层植入物用于血管生成刺激的超声波超声辐照

    公开(公告)号：US08515524B2

    公开(公告)日：2013-08-20

    申请号：US12325678

    申请日：2008-12-01

    申请人： Tsutomu Furuzono ,  Miwa Masuda ,  Masahiro Okada ,  Naotaka Nitta ,  Takashi Yamane

    发明人： Tsutomu Furuzono ,  Miwa Masuda ,  Masahiro Okada ,  Naotaka Nitta ,  Takashi Yamane

    IPC分类号： A61B5/00

    CPC分类号： A61B90/40 ,  A61N7/00

    摘要： The present invention solves the issue of bacterial infection by medical devices such as intracorporeal indwelling catheters. The present invention relates to an ultrasonic medical apparatus including a medical device (titanium oxide coated medical device 10) covered with a titanium oxide material (titanium oxide alone or a titanium oxide composite material) and ultrasonic irradiation means 20. Ultrasonic irradiation of the titanium oxide material, which exists on a surface of the medical device, causes the surface of the medical device to exert beneficial effects such as antibiotic action, the stimulation of angiogenesis, and the degradation of a blood clot and a biofilm.

    摘要翻译： 本发明解决了诸如体内留置导管之类的医疗装置的细菌感染问题。 超声波医疗装置技术领域本发明涉及一种超声波医疗装置，其包括被钛氧化物材料（单独的氧化钛或氧化钛复合材料）覆盖的医疗装置（氧化钛被覆医用器具10）和超声波照射手段20。 存在于医疗装置的表面上的材料导致医疗装置的表面发挥有益效果，例如抗生素作用，刺激血管生成以及血块和生物膜的降解。

    Boundary acoustic wave device having three-medium structure
    8.
    发明授权
    Boundary acoustic wave device having three-medium structure 有权
    具有三介质结构的边界声波装置

    公开(公告)号：US08179017B2

    公开(公告)日：2012-05-15

    申请号：US13172966

    申请日：2011-06-30

    申请人： Takashi Yamane

    发明人： Takashi Yamane

    IPC分类号： H03H9/25 ,  H01L41/08

    CPC分类号： H03H9/0222 ,  H03H9/02559

    摘要： A boundary acoustic wave device that has a three-medium structure and that prevents a high-order mode spurious response includes a piezoelectric substrate, a first dielectric layer laminated on the piezoelectric substrate, a second dielectric layer laminated on the first dielectric layer, and an IDT electrode provided at an interface between the piezoelectric substrate and the first dielectric layer. The boundary acoustic wave device utilizes a Stoneley wave that propagates along the interface. Where V1 denotes an acoustic velocity of a slow transversal bulk wave in the piezoelectric substrate and Va denotes an acoustic velocity at an anti-resonant point in a high-order mode of the Stoneley wave, Va>V1 is satisfied.

    摘要翻译： 具有三介质结构并且防止高阶模式杂散响应的弹性边界波装置包括压电基片，层压在压电基片上的第一电介质层，层叠在第一介电层上的第二电介质层和 IDT电极设置在压电基板和第一介电层之间的界面处。 边界声波装置利用沿着界面传播的斯通利波。 其中V1表示压电衬底中的慢横向体波的声速，Va表示在斯通利波的高阶模式下的反谐振点处的声速，满足Va> V1。

    Boundary acoustic wave device
    10.
    发明授权
    Boundary acoustic wave device 有权
    边界声波装置

    公开(公告)号：US08436510B2

    公开(公告)日：2013-05-07

    申请号：US12913847

    申请日：2010-10-28

    申请人： Takashi Yamane ,  Takeshi Nakao

    发明人： Takashi Yamane ,  Takeshi Nakao

    IPC分类号： H01L41/083

    CPC分类号： H01L41/18 ,  H03H9/0222 ,  H03H9/02559 ,  H03H9/02574

    摘要： A boundary acoustic wave device includes a piezoelectric substrate made of single-crystalline LiTaO3, a first medium layer disposed on the piezoelectric substrate and made of a dielectric, a second medium layer disposed on the first medium layer and made of a dielectric having a sound velocity different from that of the first medium layer, and at least one interdigital electrode disposed at the boundary between the piezoelectric substrate and the first medium layer. The sound velocity of the first medium layer is less than the sound velocity of LiTaO3. The sound velocity of the second medium layer is greater than the sound velocity of LiTaO3. The inequality (h/λ)×a≦0.05 is satisfied, where H is the thickness of the first medium layer, h is the thickness of the interdigital electrode, λ is the period of electrode fingers of the interdigital electrode, and a is the ratio of the density of a metal of the interdigital electrode to the density of Au.

    摘要翻译： 声界面波装置包括由单晶LiTaO 3构成的压电基板，设在压电基板上的第一介质层，由电介质构成，第二介质层设置在第一介质层上，由具有声速 与第一介质层的不同，以及设置在压电基板和第一介质层之间的边界处的至少一个叉指电极。 第一介质层的声速小于LiTaO3的声速。 第二介质层的声速大于LiTaO3的声速。 满足不等式（h/lambda),a@0.05），其中H是第一介质层的厚度，h是叉指电极的厚度，λ是叉指电极的电极指的周期，a是 指数电极的金属密度与Au的密度之比。