|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||416/129 ; 416/201A ; 416/237 ; 416/238|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 24 인용 특허 : 0|
The invention concerns reduction of tip vortices in aircraft propellers, wherein a fence having anhedral or dihedral is attached to the blades of the propeller. Another form of the invention is applicable to counterrotating propeller systems, wherein a fence is attached to the blades of the forward propeller of the system, and no fences are attached to the aft propeller.
An aircraft propeller system, comprising: a) forward and aft counterrotating propellers, each including a plurality of blades having curved leading edges, wherein said forward propeller blade leading edges are approximately mirror images of said aft propeller blade leading edges, except in the tip regions; b) a tip region on each of said forward propeller blades which has cahedral.