Blade for an aircraft rotor and rotor comprising such a blade

Details Blade for an aircraft rotor and rotor comprising such a blade Blade for an aircraft rotor and rotor comprising such a blade

1989-09-19

1991-07-30

Kwon, John T.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

416228, 416DIG2, 416DIG5, B64C 1118

Patent

active

050355775

ABSTRACT:
A blade is overtwisted in the extremity zone from at least 0.85R so that the resulting twist is at least equal to a limiting twist .theta.limC according to the plane form Co/C(r) of the blade in this zone and so that the lift coefficient Cz has, in a first fraction of the extremity zone extending at least between r=0/85R and r=0.9R, a decreasing value remaining lower than a first limiting value CZlim1=Czm-a(r/R-b), Czm being the mean lift coefficient of the rotor and a and b being experimental constants, and in a second extremity fraction extending between r=0.9R and at least r=0.95R, the lift coefficient continues to decrease by remaining less than or equal to a second limiting value Czlim2 linearly decreasing from the value Czlim1 for r=0.9R as far as the zero value for r=R.

REFERENCES:
patent: 3822105 (1974-07-01), Jepson
patent: 4564337 (1986-01-01), Zimmer et al.
patent: 4744728 (1988-05-01), Lednicer et al.
patent: 4880355 (1989-11-01), Vuillet et al.
patent: 4927330 (1990-05-01), Asboth

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