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1. 发明申请

US20100205805A1 TURBINE ROTOR BLADE REPAIR METHOD 有权
标题翻译：涡轮转子叶片修复方法
公开(公告)号：US20100205805A1
公开(公告)日：2010-08-19
申请号：US12670311
申请日：2009-02-09
申请人： Masahiko Mega , Kei Osawa , Masahiko Onda
发明人： Masahiko Mega , Kei Osawa , Masahiko Onda
IPC分类号： B23P6/00
CPC分类号： B23H9/10 , B23K9/044 , B23K26/32 , B23K26/342 , B23K35/0255 , B23K35/3033 , B23K2101/001 , B23K2103/18 , B23K2103/26 , B23P6/007 , B23P9/04 , F01D5/005 , F01D5/20 , F05D2230/232 , F05D2230/90 , Y10T29/49318 , Y10T29/49728 , Y10T29/49746
摘要： A turbine rotor blade repair method which reduces the occurrence of cracks due to welding is provided. A turbine rotor blade repair method for repairing damage of a fin at a tip of a turbine rotor blade includes overlaying a damaged portion of the fin with metal by welding (step S2); peening on a boundary region between the fin and the overlaying metal (step S4); and after the peening, performing solution treatment to repair the damage of the fin of the turbine rotor blade (step S6).
摘要翻译：提供了减少焊接引起的裂纹的涡轮转子叶片修复方法。涡轮转子叶片修复方法，用于修复涡轮转子叶片尖端处的翅片的损坏，包括通过焊接用金属覆盖翅片的损坏部分（步骤S2）; 在鳍状物和覆盖金属之间的边界区域上进行喷丸处理（步骤S4）; 并且在喷丸处理之后进行固溶处理以修复涡轮转子叶片的翅片的损坏（步骤S6）。

2. 发明授权

US06305641B1 Super-pressured high-altitude airship 失效
标题翻译：超级高空飞艇
公开(公告)号：US06305641B1
公开(公告)日：2001-10-23
申请号：US09536683
申请日：2000-03-28
申请人： Masahiko Onda
发明人： Masahiko Onda
IPC分类号： B64B162
CPC分类号： B64B1/62 , B64B1/26 , B64B1/38
摘要： A super-pressured high-altitude airship flies in the stratosphere, is propelled against the wind by the power obtained through the photovoltaic conversion of the sunlight, and is used for a large-scale LTA (light-than-air) platform for environmental observation, telecommunication relay, etc. This airship has a super-pressure structure which has a pressure-resistant gas bag in an envelope capable of enduring the rise of internal pressure by allowing no in-flow or out-flow of gas from or to, respectively, the outside atmosphere at the mission altitude. A solar cell is installed on an upper external surface of the envelope. A ventilation space is provided between an installation surface of the solar cell and the gas bag to block the heat transfer from the solar cell to the buoyant gas in the envelope. A fan is provided to forcibly circulate the outside atmospheric air in this ventilation space. The envelope trims the static balance of the airship pitch angle by shifting an on-board weight in the longitudinal direction.
摘要翻译：超级高空飞艇在平流层中飞行，通过太阳光转换获得的功率被推向风中，用于大规模LTA（轻空比）平台进行环境观测，电信继电器等。该飞艇具有超压结构，其在外壳中具有耐压气袋，能够耐受内部压力的上升，从而不允许气体从内向外流入或流出，在任务高度的外面气氛。太阳能电池安装在外壳的上外表面上。在太阳能电池的安装表面和气囊之间设置有通风空间，以阻挡从太阳能电池到信封中的浮力气体的传热。提供风扇以强制地将外部大气空气循环到该通风空间中。信封通过在纵向上移动车载重量来修整飞艇俯仰角的静平衡。

3. 发明授权

US07261758B2 Ni-based sintered alloy 有权
标题翻译：镍基烧结合金
公开(公告)号：US07261758B2
公开(公告)日：2007-08-28
申请号：US11012222
申请日：2004-12-16
申请人： Ikuo Okada , Kei Ohsawa , Hidetaka Oguma , Koji Takahashi , Masahiko Onda , Takeshi Seto
发明人： Ikuo Okada , Kei Ohsawa , Hidetaka Oguma , Koji Takahashi , Masahiko Onda , Takeshi Seto
IPC分类号： C22C1/04 , C22C19/05
CPC分类号： B23P6/002 , B22F1/0003 , B22F2998/00 , B22F2999/00 , C22C1/0433 , B22F3/1035
摘要： Disclosed is a Ni-based sintered alloy used for preparing a high temperature part utilized under a high temperature gas atmosphere, characterized in that the Ni-based sintered alloy is prepared by mixing and heating two kinds of Ni alloy powders differing from each other in the melting point.
摘要翻译：公开了一种用于制备在高温气氛下使用的高温部分的Ni基烧结合金，其特征在于，Ni基烧结合金通过混合和加热两种相互不同的Ni合金粉末熔点

4. 发明授权

US06655253B2 Envelope manufacturing method by braider 失效
标题翻译：信封制造方法
公开(公告)号：US06655253B2
公开(公告)日：2003-12-02
申请号：US10011312
申请日：2001-12-11
申请人： Hiroshi Uchida , Tadashi Uozumi , Masahiko Onda
发明人： Hiroshi Uchida , Tadashi Uozumi , Masahiko Onda
IPC分类号： D04C106
CPC分类号： D04C1/06 , D04C3/48 , D10B2505/18
摘要： An airship envelope manufacturing method uses a braider such that the envelope is formed as one object composed by the braider. A pair of braiding materials, whose braiding angle is ±&thgr;° to the axis, and an axial material whose angle is 0° to the axis, are organized as the braiding layer by the braider BR and the envelope En shaped like the airship is composed as one body by the braiding layer. The thickness of the braiding layer in both of the axial end parts of the airship envelope is arranged to be formed thinner than the thickness in the axial central part. The three braiding layers can be a spindle-shaped tape made of a plurality of parallel fibers having non-identical lengths, and the width of the spindle-shaped tape along the airship axis can be a function of an airship diameter along the airship axis.
摘要翻译：飞艇信封制造方法使用编织器，使得信封形成为由辫子组成的一个物体。编织编织材料的编织角度与轴线成θ°角度，角度与轴线成0°角度的轴向材料由编织物BR组成编织层，形状如飞艇组成的En 作为一个身体由编织层。飞艇围堰的两个轴向端部中的编织层的厚度被布置成比轴向中心部分的厚度更薄。三个编织层可以是由具有不同长度的多个平行纤维制成的纺锤形带，并且沿着飞艇轴线的纺锤形带的宽度可以是沿飞艇轴线的飞艇直径的函数。

5. 发明授权

US5358200A Airship 失效
标题翻译：飞艇
公开(公告)号：US5358200A
公开(公告)日：1994-10-25
申请号：US109256
申请日：1993-08-20
申请人： Masahiko Onda
发明人： Masahiko Onda
IPC分类号： B64B1/10
CPC分类号： B64B1/10
摘要： An airship includes a gas envelope filled with a buoyant gas, a duct equipped with an internal propulsion fan and attached to the aft of the gas bag, a boom projecting aft along an extension of the axis of the propulsion fan and an empennage provided on the distal end of the boom and is constituted to prevent boundary layer separation by causing the propulsion fan to suck air flowing along the hull surface into the duct and jet it aft. The duct attached to the aft of the gas bag is formed of a basket-like framework made of rigid light-weight material and covered with taut fabric material, the boom and empennage are formed of airtight fabric material and rigidified by internal pressures, and the internal pressure of the boom and the empennage are regulated so that when load forces received from the empennage side exceed prescribed values above which some part of the airship is liable to be damaged, the boom bends and/or the empennage deforms to relieve the load forces before the damage occurs and the original shape and rigidity is thereafter restored.
摘要翻译：飞艇包括填充有浮力气体的气体信封，配备有内部推进风扇并附接到气囊的后部的管道，沿着推进风扇的轴线的延伸部向后突出的悬臂，以及设置在并且构成为通过使推进风扇将沿着船体表面流动的空气吸入管道并将其向后喷射来防止边界层分离。附着在气袋后部的导管由刚性轻质材料制成的篮状框架形成，并用绷紧的织物材料覆盖，吊杆和尾翼由气密织物材料形成，并由内部压力硬化，吊臂和尾翼的内部压力受到管制，以便在从尾翼接收到的载荷力超过规定值以上时，飞艇的某些部分可能受到损坏，起重臂弯曲和/或尾翼变形以减轻载荷力在发生损坏之前，恢复原来的形状和刚度。

6. 发明申请

US20050005733A1 NI-BASED SINTERED ALLOY 有权
标题翻译：基于NI的烧结合金
公开(公告)号：US20050005733A1
公开(公告)日：2005-01-13
申请号：US10425830
申请日：2003-04-30
申请人： Ikuo Okada , Kei Ohsawa , Hidetaka Oguma , Koji Takahashi , Masahiko Onda , Takeshi Seto
发明人： Ikuo Okada , Kei Ohsawa , Hidetaka Oguma , Koji Takahashi , Masahiko Onda , Takeshi Seto
IPC分类号： F01D5/28 , B22F1/00 , C22C1/04 , C22C19/05 , F02C7/00
CPC分类号： B23P6/002 , B22F1/0003 , B22F2998/00 , B22F2999/00 , C22C1/0433 , B22F3/1035
摘要： Disclosed is a Ni-based sintered alloy used for preparing a high temperature part utilized under a high temperature gas atmosphere, characterized in that the Ni-based sintered alloy is prepared by mixing and heating two kinds of Ni alloy powders differing from each other in the melting point.
摘要翻译：公开了一种用于制备在高温气氛下使用的高温部分的Ni基烧结合金，其特征在于，Ni基烧结合金通过混合和加热两种相互不同的Ni合金粉末熔点

7. 发明授权

US08720056B2 Turbine rotor blade repair method 有权
标题翻译：涡轮转子叶片修复方法
公开(公告)号：US08720056B2
公开(公告)日：2014-05-13
申请号：US12670311
申请日：2009-02-09
申请人： Masahiko Mega , Kei Osawa , Masahiko Onda
发明人： Masahiko Mega , Kei Osawa , Masahiko Onda
IPC分类号： B23P6/04
CPC分类号： B23H9/10 , B23K9/044 , B23K26/32 , B23K26/342 , B23K35/0255 , B23K35/3033 , B23K2101/001 , B23K2103/18 , B23K2103/26 , B23P6/007 , B23P9/04 , F01D5/005 , F01D5/20 , F05D2230/232 , F05D2230/90 , Y10T29/49318 , Y10T29/49728 , Y10T29/49746
摘要： A turbine rotor blade repair method which reduces the occurrence of cracks due to welding is provided. A turbine rotor blade repair method for repairing damage of a fin at a tip of a turbine rotor blade includes overlaying a damaged portion of the fin with metal by welding (step S2); peening on a boundary region between the fin and the overlaying metal (step S4); and after the peening, performing solution treatment to repair the damage of the fin of the turbine rotor blade (step S6).
摘要翻译：提供了减少焊接引起的裂纹的涡轮转子叶片修复方法。涡轮转子叶片修复方法，用于修复涡轮转子叶片尖端处的翅片的损坏，包括通过焊接用金属覆盖翅片的损坏部分（步骤S2）; 在鳍状物和覆盖金属之间的边界区域上进行喷丸处理（步骤S4）; 并且在喷丸处理之后进行固溶处理以修复涡轮转子叶片的翅片的损坏（步骤S6）。

8. 发明授权

US06884275B2 Ni-based sintered alloy 有权
公开(公告)号：US06884275B2
公开(公告)日：2005-04-26
申请号：US10425830
申请日：2003-04-30
申请人： Ikuo Okada , Kei Ohsawa , Hidetaka Oguma , Koji Takahashi , Masahiko Onda , Takeshi Seto
发明人： Ikuo Okada , Kei Ohsawa , Hidetaka Oguma , Koji Takahashi , Masahiko Onda , Takeshi Seto
IPC分类号： F01D5/28 , B22F1/00 , C22C1/04 , C22C19/05 , F02C7/00 , C22C19/03
CPC分类号： B23P6/002 , B22F1/0003 , B22F2998/00 , B22F2999/00 , C22C1/0433 , B22F3/1035
摘要： Disclosed is a Ni-based sintered alloy used for preparing a high temperature part utilized under a high temperature gas atmosphere, characterized in that the Ni-based sintered alloy is prepared by mixing and heating two kinds of Ni alloy powders differing from each other in the melting point.

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