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公开(公告)号：EP3060383B1
公开(公告)日：2020-11-25
申请号：EP14789932.2
申请日：2014-10-03
申请人： Safran Aircraft Engines , SAFRAN
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公开(公告)号：EP3676431A1
公开(公告)日：2020-07-08
申请号：EP18773796.0
申请日：2018-08-29
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公开(公告)号：EP3060384B1
公开(公告)日：2017-10-04
申请号：EP14805978.5
申请日：2014-10-22
IPC分类号： B29B11/16 , B29C70/24 , B29C70/48 , B29C70/54 , F01D25/28 , B29C69/00 , B29C53/02 , B29C53/04 , C04B35/80 , D03D3/02 , F01D9/02 , F01D9/04 , F01D25/00 , B29L31/08
CPC分类号： F01D9/02 , B29B11/16 , B29C53/02 , B29C53/04 , B29C69/001 , B29C70/24 , B29C70/48 , B29C70/545 , B29C70/546 , B29K2713/00 , B29L2031/08 , C04B35/80 , C04B2235/3217 , C04B2235/3244 , C04B2235/3418 , C04B2235/3463 , C04B2235/3826 , C04B2235/3873 , C04B2235/5216 , D03D3/02 , F01D9/041 , F01D25/005 , F05D2220/30 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/50 , F05D2300/21 , F05D2300/2112 , F05D2300/6012 , F05D2300/6033 , F05D2300/6034 , Y02T50/672 , Y02T50/673
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公开(公告)号：EP3060383A1
公开(公告)日：2016-08-31
申请号：EP14789932.2
申请日：2014-10-03
发明人： PODGORSKI, Michael , DAMBRINE, Bruno Jacques Gerard , LE HONG, Son , COUPE, Dominique Marie Christian , MOLLIEX, Ludovic Edmond, Camille , GOERING, Jonathan
CPC分类号： F01D9/02 , B29B11/16 , B29C53/02 , B29C53/04 , B29C69/001 , B29C70/24 , B29C70/48 , B29C70/545 , B29C70/546 , B29K2713/00 , B29L2031/08 , C04B35/80 , C04B2235/3217 , C04B2235/3244 , C04B2235/3418 , C04B2235/3463 , C04B2235/3826 , C04B2235/3873 , C04B2235/5216 , D03D3/02 , F01D9/041 , F01D25/005 , F05D2220/30 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/50 , F05D2300/21 , F05D2300/2112 , F05D2300/6012 , F05D2300/6033 , F05D2300/6034 , Y02T50/672 , Y02T50/673
摘要： A fiber preform for a hollow turbine engine vane, the preform comprising a main fiber structure obtained by three-dimensional weaving and including at least one main part (41), wherein the main part (41) extends from a first link strip (44p), includes a first main longitudinal portion (46) suitable for forming essentially a pressure side wall of an airfoil, then includes an U-turn bend portion (45) suitable for forming essentially a leading edge or a trailing edge of the airfoil, then includes a second main longitudinal portion (47) facing the first main longitudinal portion (46) and suitable for forming essentially a suction side wall of the airfoil, and terminating at a second link strip (44q), wherein the first and second link strips (44p, 44q) are secured to each other and form a link portion (44) of the main fiber structure, and wherein the main longitudinal portions (46, 47) are spaced apart so as to form a gap between said main longitudinal portions (46, 47) suitable for forming a hollow in the airfoil.
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6.发明公开PREFORME FIBREUSE POUR AUBE CREUSE DE TURBOMACHINE 有权FASERVORFORMLINGFÜREINE TURBOMASCHINEN-HOHLSCHAUFEL
公开(公告)号：EP3060384A1
公开(公告)日：2016-08-31
申请号：EP14805978.5
申请日：2014-10-22
CPC分类号： F01D9/02 , B29B11/16 , B29C53/02 , B29C53/04 , B29C69/001 , B29C70/24 , B29C70/48 , B29C70/545 , B29C70/546 , B29K2713/00 , B29L2031/08 , C04B35/80 , C04B2235/3217 , C04B2235/3244 , C04B2235/3418 , C04B2235/3463 , C04B2235/3826 , C04B2235/3873 , C04B2235/5216 , D03D3/02 , F01D9/041 , F01D25/005 , F05D2220/30 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/50 , F05D2300/21 , F05D2300/2112 , F05D2300/6012 , F05D2300/6033 , F05D2300/6034 , Y02T50/672 , Y02T50/673
摘要： Fibrous preform for a hollow blade of a turbomachine, such a hollow blade and a method for manufacturing such a hollow blade. The preform comprises a first fibrous structure (41') obtained by three-dimensional weaving and comprising at least one main longitudinal portion (46, 47) able to form essentially an air foil pressure-face wall, a second fibrous structure (42') obtained by three-dimensional weaving and comprising at least one main longitudinal portion able to form essentially an air foil suction-face wall; the first and second fibrous structures (41, 42) furthermore each comprising a first connecting zone (43), extending along the front edge of their respective main longitudinal portion (46), secured to one another and forming a first connecting portion (43) of the preform and a second connecting zone (44), extending along the rear edge of their respective main longitudinal portion (46, 47), secured one to the other and forming a second connecting portion of the preform (44); the main longitudinal portions (46, 47) of the first and second fibrous structures (41', 42') being non-attached so as to leave between said main longitudinal portions (46, 47) a space (D2) able to form an air foil hollow.
摘要翻译： 提供了一种用于中空涡轮发动机叶片的纤维预制件，以及制造这种中空叶片的方法。 预型件包括第一纤维结构，其包括用于形成翼型的压力侧壁的主纵向部分; 第二纤维结构，其包括用于形成所述翼型件的吸入侧壁的主纵向部分; 第一和第二纤维结构中的每一个包括沿其主纵向部分的前边缘延伸的第一连接区域，该第一区域彼此成一体并形成第一互连部分，并且第二互连区域沿着 其主纵向部分，第二区域彼此成一体并形成第二互连部分。 第一和第二纤维结构的主要纵向部分被解离，以便在形成翼型空心的主要纵向部分之间留下间隙。
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