发明名称 HIGH MODULUS HYBRID MATERIAL ROTOR BLADE SPAR
摘要 A composite spar having an upper and edge regions is provided including a plurality of first laminates and a plurality of second laminates. The plurality of first laminates includes one or more intermediate modulus graphite plies having an intermediate modulus. The plurality of first laminates is arranged in one or more intermediate modulus layers to form at least a portion of the upper wall region, lower wall region, leading edge region and trailing edge region. The plurality of second laminates includes one or more high modulus graphite plies having a high modulus. The plurality of second laminates is arranged in one or more high modulus layers. The high modulus layers are generally interposed between intermediate modulus layers.
申请公布号 US2016208616(A1) 申请公布日期 2016.07.21
申请号 US201414915162 申请日期 2014.08.07
申请人 SIKORSKY AIRCRAFT CORPORATION 发明人 DARROW, Jr. David A.
分类号 F01D5/14;B29C70/20;B29C70/30 主分类号 F01D5/14
代理机构 代理人
主权项 1. A composite spar having an upper and lower wall region connected by leading and trailing edge regions, the spar comprising: a plurality of first laminates including one or more plies of graphite fibers having an intermediate modulus, the plurality of first laminates being arranged in one or more intermediate modulus layers, the intermediate modulus layers forming at least a portion of the upper wall region, the lower wall region, the leading edge conic region and the trailing edge conic region; and a plurality of second laminates including one or more plies of graphite fibers having a high modulus which is higher than the intermediate modulus, the plurality of second laminates being arranged in one or more high modulus layers, the high modulus layers being generally interposed between intermediate modulus layers.
地址 Stratford CT US