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1. 发明授权

EP2832638B1 HIGH-LIFT DEVICE FOR FLIGHT VEHICLE 有权
标题翻译：用于飞行器的高升力装置
公开(公告)号：EP2832638B1
公开(公告)日：2018-03-07
申请号：EP13768891.7
申请日：2013-03-29
申请人： The Society of Japanese Aerospace Companies , Kawasaki Jukogyo Kabushiki Kaisha
发明人： ISOTANI, Kazuhide , HAYAMA, Kenji
IPC分类号： B64C9/18 , B64C9/14 , B64C9/02 , B64C21/08
CPC分类号： B64C21/08 , B64C3/50 , B64C9/02 , B64C9/18 , B64C2009/143 , B64C2230/14 , Y02T50/166
摘要： A high-lift device (3) comprises a flap body (11) which is provided at a rear portion of a main wing (2) which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing (2); and a gap increasing section (20, 30) provided at an end portion (11a) of the flap body (11) in an extending direction of the flap body, to increase a gap between the rear portion of the main wing (2) and a front portion of the flap body (11) in a state in which the flap body is deployed.

2. 发明公开

EP3028942A1 METHOD OF ATTENUATING NOISE IN AIRCRAFT, LANDING GEAR STRUCTURE OF AIRCRAFT, AND AIRCRAFT 有权
标题翻译：程序中的噪声飞机减速，飞机和飞机的底盘结构
公开(公告)号：EP3028942A1
公开(公告)日：2016-06-08
申请号：EP16000043.6
申请日：2010-03-26
申请人： The Society of Japanese Aerospace Companies , KAWASAKI JUKOGYO KABUSHIKI KAISHA , Sumitomo Precision Products Co., Ltd.
发明人： ISOTANI, Kazuhide , HAYAMA, Kenji , KUMADA, Toshiyuki , ONO, Masaru
IPC分类号： B64C23/00 , B64C25/10 , B64F5/00
CPC分类号： B64C25/001 , B64C2025/003 , B64F5/00 , Y10T29/49764
摘要： A method of attenuating noise of aircraft comprises researching a static pressure and an airflow velocity in a region in the vicinity of an original shape of a designed object as a flow field characteristic of the region in the vicinity of the original shape (S5), and adding a plate-shaped object for covering a surface of the original shape which is different from a surface of the original shape facing an upstream side in an airflow direction (S7) to increase the static pressure in the region in the vicinity of the original shape to reduce the airflow velocity, thereby attenuating aerodynamic noise of the designed object.
摘要翻译：衰减飞机的噪声的方法包括：研究在一个设计对象作为原始形状（S5）附近的区域的流场特性的原始形状的附近的区域中的静压力和气流速度，并添加的板状对象用于覆盖原始形状所有这些是从在上游侧朝下的原来的形状的表面不同的在气流方向上的一个表面（S7），以增加静压力在该区域中的原始形状的附近以降低气流速度，由此衰减所设计的对象的气动噪声。

3. 发明公开

EP2415670A4 METHOD OF REDUCING NOISE OF AIR VEHICLE, LEG STRUCTURE OF AIR VEHICLE AND AIR VEHICLE 有权
标题翻译：降噪方法用于飞机，腿部结构用于飞机和飞机
公开(公告)号：EP2415670A4
公开(公告)日：2014-03-12
申请号：EP10761366
申请日：2010-03-26
申请人： SOCIETY OF JAPANESE AEROSPACE COMPANIES , KAWASAKI HEAVY IND LTD , SUMITOMO PRECISION PROD CO
发明人： ISOTANI KAZUHIDE , HAYAMA KENJI , KUMADA TOSHIYUKI , ONO MASARU
IPC分类号： B64C23/00 , B64C25/10 , B64F5/00
CPC分类号： B64C25/001 , B64C2025/003 , B64F5/00 , Y10T29/49764

4. 发明公开

EP2696030A1 TURBINE VANE 有权转让
标题翻译： TURBINENSCHAUFEL
公开(公告)号：EP2696030A1
公开(公告)日：2014-02-12
申请号：EP12768226.8
申请日：2012-04-06
申请人： IHI Corporation , The Society of Japanese Aerospace Companies
发明人： OKITA, Yoji
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/186 , F05D2250/12 , F05D2250/14 , F05D2250/52 , F05D2250/70 , F05D2260/202 , Y02T50/676
摘要： A plurality of film cooling holes (11) are formed, so as to communicate with a front cooling passage (7), in a vane surface (3a) on the front-edge side of a stator vane body (3) of a turbine stator vane (1). The hole cross-section of each of the film cooling holes (11) has a rectangular long-hole shape extending in a direction (PD) parallel to the cross-section along the span direction (SD) and having a rounded corner. The hole-center line (11c) of each of the film cooling holes (11) is inclined with respect to the thickness direction (TD) in the cross-section along the span direction (SD). The exit-side portion (11e) of the hole wall surface of each of the film cooling holes (11) is inclined with respect to the thickness direction (TD) by a greater degree than that of the hole-center line (11c).
摘要翻译：在涡轮定子的定子叶片体（3）的前缘侧的叶片面（3a）中形成有多个薄膜冷却孔（11），与前部冷却通路（7）连通，叶片（1）。每个薄膜冷却孔（11）的孔横截面具有沿与跨度方向（SD）的横截面平行的方向（PD）延伸并且具有圆角的矩形长孔形状。每个薄膜冷却孔（11）的孔中心线（11c）在跨度方向（SD）的横截面中相对于厚度方向（TD）倾斜。每个膜冷却孔（11）的孔壁面的出口侧部分（11e）相对于厚度方向（TD）比空心中心线（11c）的倾角更大程度地倾斜。

5. 发明授权

EP2692632B1 HIGH-LIFT DEVICE OF FLIGHT VEHICLE 有权
公开(公告)号：EP2692632B1
公开(公告)日：2019-09-04
申请号：EP12764943.2
申请日：2012-03-28
申请人： The Society of Japanese Aerospace Companies , Kawasaki Jukogyo Kabushiki Kaisha
发明人： ISOTANI, Kazuhide , HAYAMA, Kenji
IPC分类号： B64C21/02 , B64C9/16 , B64C9/28 , B64C9/18

6. 发明公开

EP2787173A4 TURBINE BLADE 有权
标题翻译： TURBINENSCHAUFEL
公开(公告)号：EP2787173A4
公开(公告)日：2015-07-29
申请号：EP12852740
申请日：2012-11-30
申请人： IHI CORP , SOCIETY OF JAPANESE AEROSPACE COMPANIES
发明人： OKITA YOJI , MURATA AKIRA
IPC分类号： F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F01D5/18 , F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/127 , F05D2240/304 , F05D2240/31 , F05D2260/2212 , F05D2260/2214 , Y02T50/673 , Y02T50/676
摘要： A turbine blade has hollowness, and is provided with a back-side wall of which a portion of the inner wall surface is exposed at the rear edge portion, with cooling air flown along the inner wall surface at the exposed region; and a recess provided in the inner wall surface at the exposed region. The contour of the recess (5) viewed from the normal direction of the inner wall surface of the back-side wall is set to a shape that is symmetrical centered on a reference axis (L) that intersects the flow direction of cooling air, and that broadens along the reference axis (L).
摘要翻译：涡轮叶片具有中空度，并且设置有后壁，内壁表面的一部分在后边缘部分处露出，冷却空气沿着暴露区域的内壁表面流动; 以及设置在所述暴露区域的内壁表面中的凹部。从后侧壁的内壁面的法线方向观察的凹部（5）的轮廓被设定为与冷却风的流动方向相交的基准轴（L）对称的形状，其沿着参考轴线（L）变宽。

7. 发明授权

EP2136033B1 WALL OF TURBO MACHINE AND TURBO MACHINE 有权
标题翻译： WALL透平机和涡轮机
公开(公告)号：EP2136033B1
公开(公告)日：2014-12-31
申请号：EP08739299.9
申请日：2008-03-28
申请人： IHI Corporation , The Society of Japanese Aerospace Companies
发明人： MITSUHASHI, Katsunori , TAKAHASHI, Akira , HAMAZAKI, Hiroshi , YAMAWAKI, Ruriko
IPC分类号： F01D5/14
CPC分类号： F01D5/143 , F05D2240/11 , F05D2240/80 , F05D2250/184 , F05D2250/611 , F05D2250/711 , Y02T50/673

8. 发明公开

EP2692632A1 HIGH-LIFT DEVICE FOR AIRCRAFT 有权
标题翻译：高升力装置 - 飞机
公开(公告)号：EP2692632A1
公开(公告)日：2014-02-05
申请号：EP12764943.2
申请日：2012-03-28
申请人： The Society of Japanese Aerospace Companies , Kawasaki Jukogyo Kabushiki Kaisha
发明人： ISOTANI, Kazuhide , HAYAMA, Kenji
IPC分类号： B64C9/16 , B64C23/00
CPC分类号： B64C9/18 , B64C3/58 , B64C9/16 , B64C9/28 , B64C21/02 , B64C2230/22 , Y02T50/166 , Y02T50/44
摘要： A high-lift device (3) of a flight vehicle includes: a flap main body (11) provided at a trailing edge portion of a main wing (2) of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing (2); and a vortex suppressing portion (100, 200, 300, 400, 500, or 600) provided at a tip end portion of the flap main body (11) in a wing span direction of the flap main body (11) and configured to suppress a vortex rolling up from a lower surface of a tip end portion (11a) of the flap main body (11) to an upper surface of the tip end portion (11a).

9. 发明公开

EP2415693A1 COMPOSITE TANK, MANUFACTURING METHOD THEREFOR, AND WING 有权
标题翻译： VERBUNDTANK，HERSTELLUNGSVERFAHRENDAFÜRUNDFLÜGEL
公开(公告)号：EP2415693A1
公开(公告)日：2012-02-08
申请号：EP10758416.1
申请日：2010-03-17
申请人： Mitsubishi Heavy Industries, Ltd. , THE SOCIETY OF JAPANESE AEROSPACE COMPANIES
发明人： YAMAGUCHI, Hiroaki , KAMINO, Yuichiro , NAKAMURA, Koichi , HASHIGAMI, Tooru
IPC分类号： B65D90/46 , B64D37/06
摘要： Disclosed is a composite tank that can curb static buildup, corrosion, and strength degradation. Also disclosed are a wing provided with said composite tank and a method for manufacturing the composite tank. The composite tank is characterized by being provided with: a tank body, inside which combustible material is stored, having a first resin part (11, 12) formed from fiber-reinforced resin as well as a metal part formed from metal; a second resin part (22) comprising fiber-reinforced resin and covering at least the arena of the first resin part (11, 12), on the inner surface of the tank body, that adjoins the metal part; and multiple conductive parts (23) that enable transfer of charge to the first resin part (11, 12) from the surface of the second resin part (22) that is in contact with the combustible material. The fibers included in the second resin part (22) have higher electrical resistance than the fibers included in the first resin part (11, 12). The second resin part (22) forms a layer that isolates the first resin part (11, 12) and the metal part from each other.
摘要翻译：公开了一种可以抑制静电积聚，腐蚀和强度退化的复合罐。还公开了设置有所述复合罐的翼和用于制造复合罐的方法。该复合罐的特征在于：具有储存有可燃材料的罐主体，具有由纤维增强树脂形成的第一树脂部分（11,12）以及由金属形成的金属部分; 第二树脂部分（22），包括纤维增强树脂，并且在所述罐体的内表面上至少覆盖所述第一树脂部分（11,12）的所述竞技场，所述第二树脂部分邻接所述金属部分; 以及能够从与可燃材料接触的第二树脂部件（22）的表面向第一树脂部件（11,12）传输电荷的多个导电部件（23）。包含在第二树脂部分（22）中的纤维具有比包含在第一树脂部分（11,12）中的纤维更高的电阻。第二树脂部件（22）形成使第一树脂部（11,12）和金属部彼此分离的层。

10. 发明公开

EP1911855A1 Laser peening apparatus 有权转让
标题翻译：激光喷丸-Gerät
公开(公告)号：EP1911855A1
公开(公告)日：2008-04-16
申请号：EP07117696.0
申请日：2007-10-02
申请人： Fuji Jukogyo Kabushiki Kaisha , The Society of Japanese Aerospace Companies
发明人： Adachi, Takafumi c/o Fuji Jukogyo Kabushiki Kaisha , Ogisu, Toshimichi c/o Fuji Jukogyo Kabushiki Kaisha
IPC分类号： C21D10/00 , B23K26/00
CPC分类号： C21D10/005 , B23K26/0069 , B23K26/1224 , C21D7/06
摘要： Disclosed is a laser peening apparatus, including: a liquid holding head to shape and hold liquid to trap plasma on a local surface of a workpiece; and a laser irradiation head to irradiate the surface with laser through the liquid held in the liquid holding head.
摘要翻译：本发明公开了一种激光喷丸装置，包括：液体保持头，用于成形和保持液体以将等离子体捕获在工件的局部表面上; 以及激光照射头，通过保持在液体保持头中的液体用激光照射表面。

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