Propeller blade for a turbomachine

Patent metadata

Field	Value
Publication number	US-10035582-B2
Application number	US-201314649736-A
Country	US
Kind code	B2
Filing date	Dec 5, 2013
Priority date	Dec 7, 2012
Publication date	Jul 31, 2018
Grant date	Jul 31, 2018

Abstract

A propeller blade extending radially between a blade root and a blade tip and having a leading edge and a trailing edge, together with a pressure side face and a suction side face. Along the leading edge, the angle (α) between the radial direction and a tangent to the leading edge passes through a local maximum z max situated in the range 60% to 80% of the height of the blade. Furthermore, the suction side face of the blade includes an indentation extending axially from the leading edge to the trailing edge and located at a height of the blade between the local maximum z max and the blade tip.

First claim

The invention claimed is:

1. A blade for mounting on a propeller, the blade extending radially in a height direction from a blade root to a blade tip and having a leading edge and a trailing edge, together with a pressure side face and a suction side face,
wherein, along the leading edge, an angle between a radial direction of the blade corresponding to a radial direction of the propeller on which the blade is to be mounted and a tangent to the leading edge passes through a local maximum situated in the range 60% to 80% of a height of the blade, and
wherein the suction side face of the blade includes an indentation of concave shape extending axially from the leading edge to the trailing edge, the indentation being entirely located at the height of the blade between the local maximum and the blade tip the blade presenting, in the radial direction towards the blade tip, a first curvature followed by a second curvature in an opposite direction from the first curvature so as to form a reversal of curvature of the blade in the radial direction, and wherein the concave shape of the indentation corresponds to the second curvature.

2. A blade according to claim 1 , wherein the local maximum is situated at 75% of the height of the blade.

3. A blade according to claim 1 , wherein the indentation presents a width, measured along the height of the blade, that is substantially constant.

4. A blade according to claim 1 , wherein the indentation has a width, measured along the height of the blade, that lies in the range 15% to 20% of the height of the blade.

5. A blade according to claim 1 , wherein a bottom of the indentation lies in the range 75% to 90% of the height of the blade.

6. A blade according to claim 1 , wherein an amount of curvature of the second curvature, measured in a tangential direction, increases going from the leading edge towards the trailing edge.

7. An unducted propeller for a turbine engine, the propeller comprising a plurality of blades according to claim 1 .

8. A turbine engine comprising at least one unducted propeller according to claim 7 .

9. A blade according to claim 1 , wherein the pressure side face of the blade includes a projection of convex shape extending axially from the leading edge to the trailing edge, and wherein the convex shape of the projection corresponds to the second curvature.

Assignees

• Snecma

Inventors

• Vlastuin Jonathan Evert
• Dejeu Clement Marcel Maurice

Classifications

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• B64C11/48 Primary

  Units of two or more coaxial propellers · CPC title

• Y02T50/66

  Cross-Sectional Technologies · mapped topic

• F05D2220/30

  in turbines · CPC title