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    • 6. 发明授权
    • Proprotor blade with leading edge slot
    • Proprotor刀片带前缘槽
    • US07594625B2
    • 2009-09-29
    • US10543222
    • 2003-01-23
    • Daniel B. RobertsonDudley E. SmithCharles L. HollimonJimmy C. NarramoreRobert B. Mullins
    • Daniel B. RobertsonDudley E. SmithCharles L. HollimonJimmy C. NarramoreRobert B. Mullins
    • B64C39/00
    • B64C11/16B64C27/467B64C29/0033
    • A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so the a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades.
    • 公开了一种具有固定的翼展方向的前缘槽(215)的推进器叶片(27a,27b,127a,127b),其位于至少在推进器的内侧部分中。 狭槽215由位于驱动器叶片的主要部分的前缘(202)上的选择性形状的凹入区域(219)中的选择性地成形的板条(217)形成。 狭槽215被选择成形,使得在推进器叶片的下翼面表面上的气流的一部分在推进器叶片的主要部分和板条(217)之间转向并在推进器的上部翼型表面处离开 刀。 本发明可以用于军用型倾转旋翼飞机(11)和民用型倾转旋翼飞机(111),只有微小的变化来适应不同形状的推进器叶片。