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1. 发明公开

EP2913179A1 CYLINDRICAL CASE AND PROCESS FOR PRODUCING CYLINDRICAL CASE 有权
标题翻译：圆柱形外壳，并产生圆柱形外壳的方法
公开(公告)号：EP2913179A1
公开(公告)日：2015-09-02
申请号：EP13849096.6
申请日：2013-10-22
申请人： IHI Corporation , IHI Aerospace Co., Ltd.
发明人： TANAKA, Agamu , MORITA, Hideo , OKUMURA, Ikuo , SHIGENARI, Yuu , HARADA, Takashi , DAN, Yusuke
IPC分类号： B29C70/06 , B29C70/10 , F01D25/24 , F02C7/00 , B29K105/08 , B29L31/30
CPC分类号： B64D29/02 , B29C33/301 , B29C70/22 , B29C70/222 , B29C70/24 , B29C70/446 , B29C70/54 , B29K2101/10 , B29K2713/00 , B29L2009/00 , B29L2022/00 , B29L2023/003 , B29L2031/7504 , B29L2031/772 , F01D21/045 , F01D25/24 , F01D25/243 , F05D2220/36 , F05D2300/603 , F05D2300/6034 , Y02T50/672
摘要： A cylindrical case includes: a case main body 10 made of a composite material of reinforcing fibers impregnated with a thermosetting resin; and a groove 12 disposed annularly at one end of the case main body 10. A peripheral wall 10a of the case main body 10 is formed by alternately laminating a biaxial fabric layer 13, which includes a biaxial fabric 13A of a non-crimp structure composed of reinforcing fiber bands 13a, 13b having an orientation angle of ±45°, and a roving layer 14, which includes a roving 14A composed of a bundle of reinforcing fibers extending along the circumferential direction. A groove wall 12a of the groove 12 is formed by alternately laminating the biaxial fabric layer 13, which continues to the case main body 10 side, and a triaxial fabric layer 15, which includes a triaxial fabric 15A of a non-crimp structure composed of reinforcing fiber bands 15a, 15b having an orientation angle of ±45° and a reinforcing fiber band 15c having an orientation angle of 0°. It is possible to secure high torsion strength and torsion rigidity of the entire cylindrical case, in a case where the cylindrical case is a fan case which is made of a composite material consisting of reinforcing fibers and a thermosetting resin as the raw material and has an annular groove.
摘要翻译：的圆筒状的壳体包括：主体部10由加强用热固性树脂浸渍的纤维的复合材料的情况下; 和槽12在壳体主体10的主体10是通过层压双轴替代地织物层13，其包括由非卷曲结构的双轴织物13A形成的情况下的周壁10a的一个端部环状设置的增强纤维带13A，13B在±45°取向角，和粗纱层14，其包括增强纤维沿圆周方向延伸的束构成的粗纱14A具有。槽12的槽壁12a由双轴织物层13，它继续主体10侧的情况下，和三轴织物层15，其包括由非卷曲结构的三轴织物15A交替层叠FORMED 增强纤维条带15A，15B具有±45°取向角，并具有以0°取向角的增强纤维带15c中。因此能够确保高抗扭强度和整个筒状壳体的扭转刚度，在圆筒状的壳体是一个风扇壳体所有这些由复合材料由增强纤维和热固性树脂作为原料，并且具有这样的情况环形设计槽。

2. 发明授权

EP2270337B1 METHOD FOR MANUFACTURING A BLADE OF A GAS TURBINE ENGINE FOR AN AIRPLANE 有权
标题翻译：用于动叶燃气涡轮发动机用于飞机
公开(公告)号：EP2270337B1
公开(公告)日：2013-11-20
申请号：EP09725734.9
申请日：2009-03-27
申请人： IHI Corporation , IHI Aerospace Co., Ltd.
发明人： MURAKAMI, Tsutomu , MORITA, Hideo , OGI, Takahiro , OKUMURA, Ikuo , MORIYA, Katsuyoshi
IPC分类号： F01D5/28 , B29C70/46 , B29K101/12 , B29L31/08 , B29K105/08
CPC分类号： F01D5/282 , B29C70/30 , B29C70/46 , B29D99/0025 , B29K2105/0872 , B29L2031/082 , B29L2031/087 , F01D5/141 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2230/26 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/673 , Y10T29/49336
摘要： A gas turbine engine blade for aircraft which has a 3-dimensional blade surface shape twisted around a center line at an angle of 45 degrees or more and 70 degrees or less, wherein the aforementioned blade is provided with multiple composite material prepregs which contain reinforced fiber and which are integrally molded after being laminated in the thickness direction, and the aforementioned reinforced fiber runs continuously without interruption within each layer of the aforementioned composite material prepregs.

3. 发明授权

EP3085940B1 FAN CASE AND FAN CASE MANUFACTURING METHOD 有权
公开(公告)号：EP3085940B1
公开(公告)日：2019-01-30
申请号：EP14872614.4
申请日：2014-11-14
申请人： IHI Corporation , IHI Aerospace Co., Ltd.
发明人： TANAKA, Agamu , MORI, Yuji , HARADA, Takashi , OKUMURA, Ikuo , ISHIMOTO, Kenji
IPC分类号： F02K1/80 , F01D25/00 , F01D25/24 , F02C7/00 , F02K1/64 , F02K3/02

4. 发明公开

EP3144499A1 CYLINDRICAL CASE 审中-公开
标题翻译： ZYLINDRISCHESGEHÄUSE
公开(公告)号：EP3144499A1
公开(公告)日：2017-03-22
申请号：EP14900212.3
申请日：2014-08-22
申请人： IHI Corporation , IHI AEROSPACE CO., LTD.
发明人： TANAKA, Agamu , MORI, Yuji , HARADA, Takashi , OKUMURA, Ikuo , ISHIMOTO, Kenji
IPC分类号： F02C7/00 , F02C7/04 , F04D29/42 , F04D29/52
CPC分类号： F04D29/522 , F01D25/24 , F02K1/70 , F02K3/06 , F04D29/023 , F05D2230/53 , F05D2240/91 , F05D2260/30 , F05D2260/36 , F05D2300/173 , F05D2300/174 , F05D2300/603 , Y02T50/672
摘要： A cylindrical case main body 10, and a connecting ring body 20 fitted and fixed to a first end of the case main body 10 and having an annular groove 21 open in the centrifugal direction, are provided. The connecting ring body 20 has a notch 22 open to a side opposite to a second end of the case main body 10. Into the notch 22 of the connecting ring body 20, a reinforcement body 30 is fitted, and the reinforcement body 30 has an arc-shaped groove 31 continuing to the annular groove 21 of the connecting ring body 20 in a state where the reinforcement body 30 is fitted into the notch 22 of the connecting ring body 20. In addition to attaining high rigidity, reduction in weight and reduction in manufacturing cost can also be achieved.
摘要翻译：一个圆筒形的壳体主体10和一个连接环体20，该连接环主体20装配并固定到壳体主体10的第一端并且具有沿离心方向敞开的环形槽21。连接环主体20具有与壳主体10的第二端相反的一侧开口的切口22.在连接环主体20的切口22中，配合有加强体30，加强体30具有在加强体30嵌入连接环体20的切口22的状态下，连续环状体20的环状槽21的弧形槽31除了获得高刚性，减轻重量和还原之外在制造成本上也可以实现。

5. 发明公开

EP3085940A1 FAN CASE AND FAN CASE MANUFACTURING METHOD 有权
标题翻译： VERTILATORGEHÄUSEUND VERFAHREN ZUR HERSTELLUNG DESVENTILATORGEHÄUSES
公开(公告)号：EP3085940A1
公开(公告)日：2016-10-26
申请号：EP14872614.4
申请日：2014-11-14
申请人： IHI Corporation , IHI Aerospace Co., Ltd.
发明人： TANAKA, Agamu , MORI, Yuji , HARADA, Takashi , OKUMURA, Ikuo , ISHIMOTO, Kenji
IPC分类号： F02K1/80 , F01D25/00 , F01D25/24 , F02C7/00 , F02K1/64 , F02K3/02
CPC分类号： F04D29/526 , F01D25/243 , F02K1/64 , F02K1/82 , F05D2220/323 , F05D2230/21 , F05D2230/60 , F05D2260/36 , F05D2300/121 , F05D2300/174 , F05D2300/603 , Y02T50/672
摘要： A cylindrical case body 10 made of a composite material; a linking ring 20 made of Al, which is fitted and fixed to a rear end portion of the case body 10 and has an annular groove 21 which receives a reverse thrust load from a reverse thrust transmission body 8; and ring constituent bodies 30 made of Ti alloy, each of which is placed in the rear end portion of the case body 10 and has an arcuate groove 31 which undertakes a reverse thrust load larger than that received by the linking ring 20, are included. The ring constituent bodies 30 are fitted in notches 22 of the linking ring 20 and are brought into contact with, and are fixed to, outward receiving walls 23 of the linking ring 20, whereby the ring constituent bodies 30 are positioned relative to the case body 10 in the axis CL direction and in the radial direction respectively, and the annular groove 21 and the arcuate grooves 31 are allowed to continue to each other. The ring constituent bodies made of Ti alloy, which receive a large reverse thrust load, can be placed with high positioning accuracy. Further, it is possible to allow the ring constituent bodies to undertake the reverse thrust load evenly.
摘要翻译：由复合材料制成的圆柱形壳体10; 由铝制成的连接环20，其被安装并固定到壳体10的后端部，并且具有从反向推力传递体8接收反向推力载荷的环形槽21; 以及由Ti合金构成的环状构成体30，其各自被配置在壳体10的后端部，并且具有承受比由连接环20接收的反推力负荷大的反向推力负荷的弓形槽31。环状构成体30嵌合于连结环20的切口22，与连结环20的外侧的接收壁23接触并固定，由此环状构成体30相对于壳体 10分别在CL轴方向和径向方向上，并且环形槽21和弧形槽31被允许彼此继续。能够以高定位精度放置接受大的反向推力负载的由Ti合金制成的环构成体。此外，可以使环构成体均匀地承受反向推力负荷。

6. 发明授权

EP2913179B1 CYLINDRICAL CASE AND PROCESS FOR PRODUCING CYLINDRICAL CASE 有权
标题翻译：圆柱壳和生产圆柱壳的方法
公开(公告)号：EP2913179B1
公开(公告)日：2018-01-03
申请号：EP13849096.6
申请日：2013-10-22
申请人： IHI Corporation , IHI Aerospace Co., Ltd.
发明人： TANAKA, Agamu , MORITA, Hideo , OKUMURA, Ikuo , SHIGENARI, Yuu , HARADA, Takashi , DAN, Yusuke
IPC分类号： B29C70/06 , B29C70/10 , F01D25/24 , F02C7/00 , B29K105/08 , B29L31/30
CPC分类号： B64D29/02 , B29C33/301 , B29C70/22 , B29C70/222 , B29C70/24 , B29C70/446 , B29C70/54 , B29K2101/10 , B29K2713/00 , B29L2009/00 , B29L2022/00 , B29L2023/003 , B29L2031/7504 , B29L2031/772 , F01D21/045 , F01D25/24 , F01D25/243 , F05D2220/36 , F05D2300/603 , F05D2300/6034 , Y02T50/672
摘要： A cylindrical case includes: a case main body 10 made of a composite material of reinforcing fibers impregnated with a thermosetting resin; and a groove 12 disposed annularly at one end of the case main body 10. A peripheral wall 10a of the case main body 10 is formed by alternately laminating a biaxial fabric layer 13, which includes a biaxial fabric 13A of a non-crimp structure composed of reinforcing fiber bands 13a, 13b having an orientation angle of ±45°, and a roving layer 14, which includes a roving 14A composed of a bundle of reinforcing fibers extending along the circumferential direction. A groove wall 12a of the groove 12 is formed by alternately laminating the biaxial fabric layer 13, which continues to the case main body 10 side, and a triaxial fabric layer 15, which includes a triaxial fabric 15A of a non-crimp structure composed of reinforcing fiber bands 15a, 15b having an orientation angle of ±45° and a reinforcing fiber band 15c having an orientation angle of 0°. It is possible to secure high torsion strength and torsion rigidity of the entire cylindrical case, in a case where the cylindrical case is a fan case which is made of a composite material consisting of reinforcing fibers and a thermosetting resin as the raw material and has an annular groove.

7. 发明公开

EP2913178A1 CYLINDRICAL CASE AND METHOD FOR MANUFACTURING CYLINDRICAL CASE 有权
标题翻译： ZYLINDRISCHERBEHÄLTERUND VERFAHREN ZUR HERSTELLUNG DES ZYLINDRISCHENBEHÄLTERS
公开(公告)号：EP2913178A1
公开(公告)日：2015-09-02
申请号：EP13848822.6
申请日：2013-10-22
申请人： IHI Corporation , IHI Aerospace Co., Ltd.
发明人： MURAKAMI, Tsutomu , OKUMURA, Ikuo , SHIGENARI, Yuu , HARADA, Takashi , DAN, Yusuke
IPC分类号： B29C70/06 , B29C70/10 , F01D25/24 , F02C7/00 , B29K105/08 , B29L31/30
CPC分类号： F01D25/243 , B29C70/222 , B29C70/446 , B29L2031/7504 , B32B37/10 , B32B37/18 , B32B38/0012 , B32B38/08 , B32B2305/08 , B32B2305/18 , F01D21/045 , F01D25/005 , F01D25/24 , F02K3/06 , F05D2220/40 , F05D2300/44 , F05D2300/603 , F05D2300/611 , F05D2300/614 , Y02T50/672 , Y10T156/1051
摘要： A cylindrical case includes a case main body 9C made of a composite material of reinforcing fibers impregnated with a thermosetting resin, and an outward flange 10 on the case main body 9C. The outward flange 10 includes: a bonding layer 11c to be bonded; a foundation layer 12 disposed on the bonding layer 11c; one flange constituting layer 13 having a leg layer 13a which is laminated from one slope surface 12a of the foundation layer 12 to the bonding layer 11c and a wall layer 13b which rises from the one slope surface 12a; and the other flange constituting layer 11 having a leg layer 11a which is laminated from the other slope surface 12b of the foundation layer 12 to the bonding layer 11c and a wall layer 11b which rises from the other slope surface 12b. The foundation layer 12 is formed by laminating roving layers, while the flange constituting layers 11, 13 are formed by laminating a plurality of biaxial fabric layers including a biaxial fabric 15 of a non-crimp structure. It is possible to secure high structural strength of the outward flange of a fan case which is made of a composite material consisting of reinforcing fibers and a thermosetting resin as the raw material.
摘要翻译：圆筒形壳体包括由浸渍有热固性树脂的增强纤维的复合材料和壳体主体9C上的向外凸缘10制成的壳体主体9C。向外凸缘10包括：待接合的粘结层11c; 设置在接合层11c上的基底层12; 一个凸缘构成层13，其具有从基础层12的一个倾斜表面12a到接合层11c层压的腿部层13a和从一个倾斜表面12a上升的壁层13b; 另一个凸缘构成层11具有从基础层12的另一个倾斜表面12b到接合层11c层压的腿部层11a和从另一个倾斜表面12b上升的壁层11b。基底层12通过层叠粗纱层而形成，而凸缘构成层11,13通过层叠多个包括非卷曲结构的双轴织物15的双轴织物层而形成。可以确保由作为原料的由增强纤维和热固性树脂组成的复合材料制成的风扇壳体的向外凸缘的高结构强度。

8. 发明公开

EP2270337A1 BLADE OF A GAS TURBINE ENGINE FOR AN AIRPLANE, AND A METHOD FOR MANUFACTURING THE SAME 有权
标题翻译： HERSTELLUNGSVERFAHRENFÜREINE LAUFSCHAUFEL EINER GASTURBINENMOTORSFÜREIN FLUGZEUG
公开(公告)号：EP2270337A1
公开(公告)日：2011-01-05
申请号：EP09725734.9
申请日：2009-03-27
申请人： IHI Corporation , IHI Aerospace Co., Ltd.
发明人： MURAKAMI, Tsutomu , MORITA, Hideo , OGI, Takahiro , OKUMURA, Ikuo , MORIYA, Katsuyoshi
IPC分类号： F04D29/38 , B29C43/20 , B29K101/12 , B29K105/08 , B29L31/30
CPC分类号： F01D5/282 , B29C70/30 , B29C70/46 , B29D99/0025 , B29K2105/0872 , B29L2031/082 , B29L2031/087 , F01D5/141 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2230/26 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/673 , Y10T29/49336
摘要： A gas turbine engine blade for aircraft which has a 3-dimensional blade surface shape twisted around a center line at an angle of 45 degrees or more and 70 degrees or less, wherein the aforementioned blade is provided with multiple composite material prepregs which contain reinforced fiber and which are integrally molded after being laminated in the thickness direction, and the aforementioned reinforced fiber runs continuously without interruption within each layer of the aforementioned composite material prepregs.
摘要翻译：一种用于飞机的燃气涡轮发动机叶片，其具有以45度以上且70度以下的角度绕中心线扭转的3维叶片表面形状，其中，所述叶片设置有多个复合材料预浸料，其包含增强纤维并且在厚度方向层叠后一体成型，上述增强纤维在上述复合材料预浸料的各层内连续不间断地延伸。

9. 发明公开

EP3954907A1 JOINT STRUCTURE AND ASSEMBLY METHOD FOR SAME 有权
公开(公告)号：EP3954907A1
公开(公告)日：2022-02-16
申请号：EP19924628.1
申请日：2019-04-12
申请人： IHI Aerospace Co., Ltd.
发明人： HARADA, Takashi , SHIGENARI, Yu , OKUMURA, Ikuo , AKIMOTO, Toyoharu
IPC分类号： F16B5/06 , F16B11/00 , B64C1/06
摘要： A joint structure (10) includes a connection member (5) provided between a reinforced member (1) and a reinforcing member (3) and connecting both of them to each other. The connection member (5) includes a first coupling portion (5a) and a second coupling portion (5b) that are coupled to one and another of the reinforced member (1) and the reinforcing member (3), respectively. The first coupling portion (5a) is coupled to a joint portion (3a) of one of the reinforced member (1) and the reinforcing member (3) by an adhesive (9) or welding. The first coupling portion (5a) and the joint portion (3a) are shaped so as to be caught by each other in a joining direction (D3) in which the reinforced member (1) and the reinforcing member (3) are joined to each other.

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