Turbine engine blade, in particular for a one-piece bladed disk

Patent metadata

Field	Value
Publication number	US-9556740-B2
Application number	US-201214361594-A
Country	US
Kind code	B2
Filing date	Nov 22, 2012
Priority date	Nov 29, 2011
Publication date	Jan 31, 2017
Grant date	Jan 31, 2017

Abstract

A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.

First claim

The invention claimed is:

1. A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip, wherein the leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in a range 20% to 40% of a total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip, wherein
the sweep angle of the leading edge of the airfoil becomes negative as from a second radial height of the airfoil situated in a range 60% to 80% of the total radial height of the airfoil.

2. A blade according to claim 1 , wherein the sweep angle of the leading edge of the airfoil is less than −45 at the tip of the airfoil.

3. A blade according to claim 1 , wherein the leading edge of the airfoil presents a dihedral angle that increases generally from the root to the tip.

4. A blade according to claim 3 , wherein the dihedral angle of the leading edge of the airfoil lies between a minimum value at the root lying in a range −25° to −5°, and a maximum value at the tip lying in a range +5° to +25°.

5. A blade according to claim 4 , wherein the dihedral angle of the leading edge of the airfoil lies in a range 15° at the root to +15° at the tip.

6. A blade according to claim 3 , wherein the dihedral angle of the leading edge of the airfoil is negative between the root and the first radial height of the airfoil, and positive between a third radial height of the airfoil situated in a range 40% to 60% of the total radial height of the airfoil and the tip.

7. A blade according to claim 6 , wherein the third radial height of the airfoil is situated at 50% of the total radial height of the airfoil.

8. A blade according to claim 1 , wherein the first radial height of the airfoil is situated at 30% of the total radial height of the airfoil.

9. A one-piece bladed disk for a turbine engine, comprising a plurality of blades according to claim 1 .

10. A turbine engine, comprising at least one one-piece bladed disk according to claim 9 .

Assignees

• Snecma

Inventors

• Perrot Vincent Paul Gabriel
• Cellier Damien
• Dufresne Alicia Lise Julia
• Pelletrau Philippe Pierre Marcel Marie
• Rios Jean-Francois Antoine Christian
• Villaines Laurent Christophe Francis

Classifications

• F01D5/141 Primary

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

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2250/71

  curved · CPC title

• F04D29/324

  Blades · CPC title

• F05D2240/242

  of reaction type · CPC title