초록 ▼

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 θlimC 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

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 θlimC 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.

대표청구항 ▼

1. Blade for an aircraft rotor whose successive elementary sections along at least the larger part of the wingspan R present a constant chord Co and said elementary sections are twisted from the root of said blade towards the extremity of the latter by an angle θ whose variation dθ/dr according to t

1. Blade for an aircraft rotor whose successive elementary sections along at least the larger part of the wingspan R present a constant chord Co and said elementary sections are twisted from the root of said blade towards the extremity of the latter by an angle θ whose variation dθ/dr according to the wingspan position r of a given elementary section is constant, wherein said blade exhibits in the end zone extending at least between 0.85 R and at least 0.95 R an excess twist so that the resultant twist in said zone is less than or at the most equal as an absolute value to the limiting twist given by: ##EQU##θlim=θ+1(Czlim-Cz), (1) an equation in which k is the ratio of k the variation of the lift coefficient Cz to the variation of incidence i and Czlim is an upper limiting value for the lift coefficient Cz so that, firstly, in a first fraction of the end zone extending at least between r=0.85 R and approximatively r=0.9 R, the limiting lift coefficient has a value ##EQU##Czlim1=Czm-a(r/R-b), (2) an equation in which Czm is the mean lift coefficient of said rotor, a and b are constants at least equal to 1.6 and 0.87 respectively and being such that secondly, in a fraction of the end zone extending between approximately r=0.9 R and at least r=0.95 R, the limiting lift coefficient Czlim2 has a value linearly decreasing from the value of Czlim1 given by the equation (2) for r=0.9 R to the zero value for r=R. 2. Rotor blade according to the claim 1, wherein said first extremity zone fraction extends between r=0.7 R and approximatively r=0.9 R. 3. Rotor blade according to claim 1, wherein said second extremity zone fraction extends approximatively between r=0.9 R and r=R. 4. Rotor blade according to claim 1, so that in said first and second extremity zone fractions, said successive elementary sections exhibit an evolutive chord which is a function C(r) of the wingspan position r of a given elementary section, wherein, on the span of said first and second extremity zone fractions, the twist of said blade is, as an absolute value, advantageously at least equal to the limiting twist θlimC given by: ##EQU##θlimC=θ+1(Czlim.Co/C(r)-Cz) (3) an equation in k which the lift coefficient Czlim is selected in said extremity zone fractions to be at the most equal to a value CzlimC so that ##EQU##CzlimC=Czlim.Co/C(r), (4) an expression in which Czlim represents either Czlim1 or Czlim2 according to that of said first or second extremity zone fraction. 5. Rotor blade according to claim 1, wherein on the span of said first and second extremity zone fractions, the twist of said blade is, as an absolute value, at least equal to said limiting twist reduced by one tolerance. 6. Blade according to claim 5, wherein said tolerance is about 0.5°. 7. Rotor blade according claim 4, wherein said second extremity zone fraction is defined by the range approximatively extending from r=0.9 R to r=0.95 R and by the point r=R, a linear twist connection being embodied between r=0.95 R and r=R, regardless of the function C(r).