Rotor blade for a rotor of an aircraft designed to minimize noise emitted by the rotor

Patent metadata

Field	Value
Publication number	US-9359072-B2
Application number	US-201313775418-A
Country	US
Kind code	B2
Filing date	Feb 25, 2013
Priority date	Feb 27, 2012
Publication date	Jun 7, 2016
Grant date	Jun 7, 2016

Abstract

A blade ( 20 ) of a rotor ( 5 ), the blade ( 20 ) having a suction side ( 21 ) and a pressure side ( 22 ) extending transversely from a leading edge ( 23 ) towards a trailing edge ( 24 ) and extending spanwise from a root section ( 31 ) towards a free end section ( 41 ). The blade ( 40 ) comprises, going from the root section ( 31 ) towards said free end section ( 41 ): a root zone ( 30 ); followed by rounded zone ( 35 ); said rounded zone ( 35 ) presenting rounded pressure and suction sides ( 22″, 21 ″) departing from said main plane (P 1 ) in a direction (Z) parallel to the axis of rotation (AXROT) of said blade.

First claim

What is claimed is:

1. A blade of a rotor, the blade having a suction side and a pressure side extending transversely from a leading edge towards a trailing edge and extending spanwise from a root section towards a free end section, wherein the blade comprises spanwise from the root section towards the free end section: a root zone; and then a single rounded zone extending transversely from the leading edge towards the trailing edge; the root zone being contained in a main plane of rotation (P 1 ), the rounded zone presenting rounded pressure and suction sides from the leading edge towards the trailing edge that, starting from the root zone, depart from the main plane (P 1 ) in a direction (Z) parallel to the axis of rotation (AXROT) of the blade, and opposite to the flow direction of a fluid through the blade until a point of maximum curvature (PCO) is reached, and then come closer to the main plane (P 1 );
wherein the point of maximum curvature (PCO) lies in a secondary plane (P 3 ) upstream from the main plane (P 1 ) and parallel with the main plane (P 1 ); and
wherein a projection (PCO′) of the point of maximum curvature (PCO) onto an orthogonal plane (P 2 ) is situated at a radial distance (DR) from the root section that lies in the range one-fourth of the span (R) of the blade between the root section and the free end section and three-fourths of the span (R), the orthogonal plane (P 2 ) being perpendicular to the main plane (P 1 ) and containing a pitch variation axis (AXPAS) of the blade;
wherein the rounded zone, starting from the root zone, departs from the main plane (P 1 ) and then moves closer thereto, and the blade presents, starting from the main plane (P 1 ), an end zone that follows on from the rounded zone, the end zone including the free end section;
wherein the blade presents a plurality of sections distributed spanwise along a stacking line of the blade, and a root portion of the stacking line situated in the root zone and an end portion of the stacking line situated in the end zone are arranged in the main plane (P 1 ), with an intermediate portion of the stacking line that is situated in the rounded zone being curved to depart from the main plane (P 1 ) in a direction parallel to the axis of rotation of the blade;
wherein projections of the root portion and of the end portion onto an orthogonal plane (P 2 ) coincide with a pitch variation axis (AXPAS) of the blade in the orthogonal plane, the orthogonal plane (P 2 ) being perpendicular to the main plane (P 1 ) and containing a pitch variation axis (AXPAS) of the blade; and
wherein the projections of the root portion and the end portion extend spanwise to coincide with the pitch variation axis such that the stacking line coincides with the pitch variation axis for the root portion and the end portion.

2. A blade according to claim 1 , wherein the root zone and the end zone are arranged in the main plane (P 1 ).

3. A blade according to claim 1 , wherein a projection of the intermediate portion onto an orthogonal plane (P 2 ) has the shape of a cubic spline function, the orthogonal plane (P 2 ) being perpendicular to the main plane (P 1 ) and containing a pitch variation axis (AXPAS) of the blade.

4. The blade according to claim 3 , the cubic spline function is formed by using at least three control points, a first control point being common to the root portion and to the intermediate portion.

5. A blade according to claim 1 , wherein the point of maximum curvature (PCO) is situated at a vertical distance (DV) from the main plane (P 1 ), with the vertical distance (DV) lying in the range one-third of a reference chord (CREF) to three times the reference chord (CREF).

6. A blade according to claim 5 , wherein the point of maximum curvature (PCO) is contained in a maximum section of the blade, and the reference chord is the chord of the maximum section.

7. A blade according to claim 1 , wherein the root zone extends radially spanwise from the root section towards a first intermediate section common to the root zone and to the rounded zone, the first intermediate section being arranged radially between the root section and a middle section of the blade situated at equal distances from the root section and from the free end section.

8. A blade according to claim 1 , wherein the end zone extends radially spanwise from a second intermediate section common to the end zone and to the rounded zone towards the free end section, the second intermediate section being arranged radially between the free end section and a middle section of the blade situated at equal distances from the root section and from the free end section.

9. A rotor having a rotary hub carrying a plurality of blades, wherein each blade is a blade according to claim 1 .

10. A rotor according to claim 9 , wherein the rotor has a fairing defining a duct in which the blades move, the rotor including a guide-stator situated downstream from the blades, the rounded zone departing from the main plane (P 1 ) so as to place the point of maximum curvature farther away from the guide-stator.

11. An aircraft, including a rotor according to claim 9 .

12. The blade according to claim 1 , wherein the rounded zone decreases linearly towards the free end section between the point of maximum curvature (PCO) and the main plane (P 1 ).

13. The blade according to claim 1 , wherein the stacking line only deviates from the pitch variation axis for the single rounded zone.

Assignees

• Airbus Helicopters

Inventors

• Finck Sebastien
• Sudre Laurent

Classifications

• B64C2027/8254

  Shrouded tail rotors, e.g. "Fenestron" fans · CPC title

• B64C27/467 Primary

  Aerodynamic features · CPC title

• B64C27/46 Primary

  Blades · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title