公开(公告)号：US20150337670A1

公开(公告)日：2015-11-26

申请号：US14654390

申请日：2013-12-19

Applicant: COMPOSITE TECHNOLOGY AND APPLICATIONS LIMITED

Inventor： Nicholas Michael Merriman

IPC: F01D5/28 ,  F01D5/14

Abstract: An aerofoil structure (26) for a gas turbine engine (10), the aerofoil structure comprising a carbon composite aerofoil portion (38) and a tip portion (48), wherein the tip portion comprises a tip surface (60) configured to face a corresponding casing structure (30), the tip portion further comprising a ridge line (62) extending along at least a portion of the tip surface, wherein the tip surface comprises a first surface (64) and a second surface (66) provided either side of the ridge line, the ridge line being defined by the intersection of the first and second surfaces, wherein the ridge line is configured to cut into the casing structure during an interaction between the aerofoil structure and casing structure.

Abstract translation: 一种用于燃气涡轮发动机（10）的机翼结构（26），所述机翼结构包括碳复合机翼部分（38）和末端部分（48），其中所述尖端部分包括尖端表面（60） 相应的外壳结构（30），所述尖端部分还包括沿着所述尖端表面的至少一部分延伸的脊线（62），其中所述尖端表面包括第一表面（64）和第二表面（66） 脊线由第一和第二表面的交点限定，其中脊线被构造成在机翼结构和套管结构之间的相互作用期间切入壳体结构。