Blade end for rotary wing of an aircraft and rotary wing provide

Details Blade end for rotary wing of an aircraft and rotary wing provide Blade end for rotary wing of an aircraft and rotary wing provide

1982-05-26

1984-05-29

Marcus, Stephen

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Tined or irregular periphery

416237, B64C 2746

Patent

active

044512066

ABSTRACT:
The invention relates to a blade end for rotary wing of an aircraft, whose span is between 5 and 15% of the span of said blade. According to the invention, this blade end is charaterized in that, between points A and B', there is a stagger which, measured parallel to the span of the blade, is between 5 and 25% of the chord of the profile of the blade adjacent said blade end and in that the leading edge line of said blade end is curvilinear and such that its angle of sweep .phi. varies progressively and continuously from a low value .phi..sub.o near the blade, of between 0.degree. and 30.degree., up to a high value .phi..sub.E towards the outside of the blade, of between 60.degree. and 90.degree.. The invention leads to increased performances and to a reduction in the noise level of rotary wings.

REFERENCES:
patent: 3399731 (1968-09-01), Giles, Jr.
patent: 3467197 (1969-09-01), Spivey et al.
patent: 3721507 (1973-03-01), Monteleone
patent: 4077741 (1978-03-01), Lowson et al.
patent: 4248572 (1981-02-01), Fradenburgh
patent: 4334828 (1982-06-01), Moffitt

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