Method for modeling a non-streamlined propeller blade

Patent metadata

Field	Value
Publication number	US-10417378-B2
Application number	US-201414908399-A
Country	US
Kind code	B2
Filing date	Jul 28, 2014
Priority date	Jul 29, 2013
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A method for modeling at least a part of a blade of a non-streamlined propeller, part of the blade having an offset. The method includes (a) Parameterization of at least one Bezier curve representing a deformation of the blade characterizing the offset, defined by: a. First and second end control points (PCU1, PCUK); b. At least one intermediate control point (PCUi, i∈[[2,K−1]]) disposed between the end points (PCU1, PCUK). The parameterization being performed according to at least one deformation parameter and the cutting height in the blade, on the basis of which the abscissa of the intermediate control point (PCUi) and the ordinate of the second end point (PCUK) are expressed. Optimized values of the deformation parameter or parameters are determined and then output.

First claim

The invention claimed is:

1. A method for manufacturing a blade of a non-streamlined propeller, the method comprising:
modeling said blade, using a data processor or a piece of equipment, at least one portion of the blade having a tangential offset along a direction orthogonal to a longitudinal axis of said blade, said modeling comprising:
(a) parameterizing at least one Bezier curve representing a deformation of said blade characterizing the tangential offset, depending on a position along a section at a given height in the blade, the curve being defined by:
a. A first and second end control point (PCU1, PCUK) defining the extent of said section of the blade;
b. At least one intermediate control point (PCUi, i∈[[2,K−1]]) positioned between the end points (PCU1, PCUK),
the parameterization being performed according to at least one deformation parameter and said height of the section in the blade, as a function of which the abscissa of the intermediate control point (PCUi) and the ordinate of the second end point (PCUK) are expressed;

(b) determining optimized values of the deformation parameter(s);
(c) outputting to an interface of said piece of equipment the thereby determined values;
(d) manufacturing said blade according to the modeling of the at least one portion of the blade obtained by said modeling.

2. The method according to claim 1 , wherein the deformation parameters are a relative height at the onset of deformation (h 0 ) and a maximum offset (d max ) at the end of the blade, the at least one parameterized Bezier curve being associated with a relative height h of a section in the blade, h∈[h 0 , 1].

3. The method according to claim 2 , wherein the ordinate (y K ) of the second end control point (PCU K ) is given by

y
K

=

d
max

*

(

h
-

h
0

1
-

h
0

)

2

.

4. The method according to claim 2 , wherein the abscissa (x i ) of the at least one intermediate control point (PCU i ) is proportional to

x
rel

=

1
-

(

h
-

h
0

1
-

h
0

)

2

.

5. The method according to claim 1 , wherein K≥4, the i ith (i∈[[2, K−2]]) intermediate control points (PCU i ) being movable points for which the abscissa depends on the height of said section in the blade, the K−2 th intermediate control point (PCU K-1 ) being set.

6. The method according to claim 4 , in which the abscissa (x i ) of the K−3 movable intermediate control points (PCU i ) is given by

x

i
∈

〚

2
,

K
-
2

〛

=

x

K
-
1

*

i
-
1

K
-
3

*

x
rel

with (x K-1 ) the abscissa of the set intermediate control point (PCU K-1 ).

7. The method according to claim 6 , wherein x K-1 =0.75.

8. The method according to claim 5 , wherein K=7, so as to have four movable intermediate control points (PCU i ).

9. The method according to claim 1 , wherein the ordinate of the first end control point (PCU 1 ) and of each intermediate control point (PCU i ) is equal to zero.

10. The method according to claim 9 , wherein the derivative of the Bezier curve at the first end control point (PCU 1 ) is zero.

11. The method according to claim 1 , wherein a plurality of Bezier curves corresponding to sections at different heights in the blade is parameterized in said step (a).

12. The method according to claim 1 , wherein the optimized values determined in said step (b) are values of the deformation parameters for which the intensity of a marginal vortex generated by the blade is a minimum.

13. A non-streamlined propeller comprising a plurality of blades obtained via the method according to claim 1 .

Assignees

• Snecma
• Safran Aircraft Engines

Inventors

• Verbrugge Cyril
• Vlastuin Jonathan
• Dejeu Clement
• Louet Anthony

Classifications

• F04D27/001

  Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• G06F30/15 Primary

  Vehicle, aircraft or watercraft design · CPC title

• F04D29/324

  Blades · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title