发明名称 COMPOSITE BLADE ROOT STUCTURE
摘要 <p>A spar of a rotor blade having moderate depth transitions to a relatively much deeper shank over a relatively short distance. This rapid transition enables a low-weight blade root that is structurally efficient, offers a high moment capability, and enables high Mach number axial flow. A transition could advantageously reduce section depth by at least 15%, 20%, 30%, or even 40% over at most 5%, 6%, 10%, or 12% of a total length of the rotor blade. Such a transition could advantageously be accomplished using a cuff, which has interfaces with each of the spar and the shank. The rotor blade shank has a generally circular cross-section which allows for a rotary attachment to a hub, where the attachment may advantageously comprise a mechanical or elastomeric bearing. Preferred embodiments have a spar with a generally rectangular cross-section.</p>
申请公布号 WO2009111568(A1) 申请公布日期 2009.09.11
申请号 WO2009US36040 申请日期 2009.03.04
申请人 KAREM AIRCRAFT, INC.;GUPTA, NEIL;KAREM, ABE 发明人 GUPTA, NEIL;KAREM, ABE
分类号 F03B3/12 主分类号 F03B3/12
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