Leading edge profile of vanes

Patent metadata

Field	Value
Publication number	US-11047238-B2
Application number	US-201816478972-A
Country	US
Kind code	B2
Filing date	Jan 25, 2018
Priority date	Jan 30, 2017
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

Abstract

A vane configured to be placed with a plurality of identical vanes so as to form a vane wheel for an aeroengine, the vane wheel defining an axis, the vane having an airfoil presenting a leading edge and a trailing edge, the leading-edge curve describing the shape of the leading edge of the airfoil in a view perpendicular to the airfoil presenting at least one leading-edge undulation, said at least one leading-edge undulation extending over less than 30% of a length of the airfoil from the first end of the airfoil.

First claim

The invention claimed is:

1. A vane configured to be placed with a plurality of identical vanes so as to form a vane wheel for an aeroengine, the vane comprising a root and a tip at its ends, the vane wheel defining an axis, the vane comprising an airfoil presenting a leading edge and a trailing edge, a leading-edge curve describing the shape of the leading edge of the airfoil in a view perpendicular to the airfoil presenting at least one leading-edge undulation, said at least one leading-edge undulation extending over less than 30% of a length of the airfoil from an airfoil root and at least one leading-edge undulation extending from an airfoil tip over less than 30% of the length of the airfoil, the leading-edge curve being monotonic over the range going from 30% to 70% of the length of the airfoil, and
an angle of attack being an angle between a tangent to a camber line at the leading edge of the airfoil and the axis of the vane wheel in a view in a longitudinal direction of the airfoil, an angle-of-attack curve describing a variation of the angle of attack along the airfoil presents at least one angle-of-attack undulation extending over less than one third of the length of the airfoil from the airfoil root, and the angle-of-attack curve presenting at least one angle-of-attack undulation extending from the airfoil tip over less than one-third of the length of the airfoil;
wherein, for an undulation being a curve portion situated between two minimums and including a single maximum, at least one maximum included in an undulation of the leading-edge curve is arranged substantially at the same position in the longitudinal direction of the airfoil as a minimum defining an angle-of-attack undulation.

2. The vane according to claim 1 , wherein the angle-of-attack leading edge curve presents two or three angle-of-attack leading edge undulations extending from the airfoil root over less than one-third of the length of the airfoil, and/or two or three angle-of-attack leading edge undulations extending from the airfoil tip over less than one-third of the length of the airfoil.

3. The vane according to claim 1 , wherein the angle-of-attack curve presents two or three angle-of-attack undulations extending from the airfoil root over less than one-third of the length of the airfoil, and/or two or three angle-of-attack undulations extending from the airfoil tip over less than one-third of the length of the airfoil.

4. A vane wheel comprising a plurality of vanes according to claim 1 .

5. A vane configured to be placed with a plurality of identical vanes so as to form a vane wheel for an aeroengine, the vane comprising a root and a tip at its ends, the vane wheel defining an axis, the vane comprising an airfoil presenting a leading edge and a trailing edge, a leading-edge curve describing the shape of the leading edge of the airfoil in a view perpendicular to the airfoil presenting at least one leading-edge undulation, said at least one leading-edge undulation extending over less than 30% of a length of the airfoil from an airfoil root and at least one leading-edge undulation extending from an airfoil tip over less than 30% of the length of the airfoil, the leading-edge curve being monotonic over the range going from 30% to 70% of the length of the airfoil, and
an angle of attack being an angle between a tangent to a camber line at the leading edge of the airfoil and the axis of the vane wheel in a view in a longitudinal direction of the airfoil, an angle-of-attack curve describing a variation of the angle of attack along the airfoil presents at least one angle-of-attack undulation extending over less than one third of the length of the airfoil from the airfoil root, and the angle-of-attack curve presenting at least one angle-of-attack undulation extending from the airfoil tip over less than one-third of the length of the airfoil;
wherein, for an undulation being a curve portion situated between two minimums and including a single maximum, at least one maximum of an undulation of the leading-edge curve lies closer, in the longitudinal direction of the airfoil, to a minimum of an undulation of the angle-of-attack curve than to a maximum of the undulation of the an angle-of-attack curve.

6. The vane according to claim 5 , wherein the angle-of-attack leading edge curve presents two or three angle-of-attack leading edge undulations extending from the airfoil root over less than one-third of the length of the airfoil, and/or two or three angle-of-attack leading edge undulations extending from the airfoil tip over less than one-third of the length of the airfoil.

7. The vane according to claim 5 , wherein the angle-of-attack curve presents two or three angle-of-attack undulations extending from the airfoil root over less than one-third of the length of the airfoil, and/or two or three angle-of-attack undulations extending from the airfoil tip over less than one-third of the length of the airfoil.

8. The vane according to claim 7 , wherein at least one maximum included in an undulation of the leading-edge curve is arranged substantially at the same position in the longitudinal direction of the airfoil as a minimum defining an angle-of-attack undulation.

9. A vane wheel comprising a plurality of vanes according to claim 5 .

Assignees

• Safran Aircraft Engines

Inventors

• Guegan Damien Bernard Emeric
• Cojande Prasaad
• Retiveau Pierre-Hugues Ambroise Maxime Victor
• Vlastuin Jonathan Evert

Classifications

• F04D29/324

  Blades · CPC title

• F01D5/141 Primary

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

• F05D2240/121

  related to the leading edge of a stator vane · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F05D2250/611

  undulated · CPC title