Turbine engine blade

Patent metadata

Field	Value
Publication number	US-9638049-B2
Application number	US-201414228409-A
Country	US
Kind code	B2
Filing date	Mar 28, 2014
Priority date	Apr 2, 2013
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

A turbine engine blade includes an airfoil connected by a platform to a middle radial wall extending axially and prolonged radially inwards by a blade root that is mountable in a slot of a disk, and the platform and the middle radial wall defining two lateral cavities situated on either side of the middle radial wall and opening out circumferentially to receive scaling members. The cavities are open downstream with two fins projecting on either side of the middle radial wall at downstream end of the middle radial wall, the fins coming to bear against two adjacent teeth of the disk between which the slot is formed. The downstream end of the middle radial wall includes a setback extending between at least one rib of the platform and the fins.

First claim

The invention claimed is:

1. A turbine engine blade comprising:
an airfoil connected by a platform to a middle radial wall extending axially and prolonged radially inwards by a blade root that is mountable in a slot of a disk, and
the platform and said middle radial wall defining two lateral cavities situated on either side of said middle radial wall and opening out circumferentially to receive sealing members, wherein
said cavities are open downstream with two fins projecting on either side of said middle radial wall at a downstream end of said middle radial wall, said fins coming to bear against two adjacent teeth of the disk between which the slot is formed, and wherein
the downstream end of the middle radial wall includes a setback extending between at least one rib of the platform and the fins.

2. The blade according to claim 1 , wherein a ratio L/l of a length L of the setback, wherein L is a maximum dimension of the setback in a longitudinal direction of the airfoil, divided by a width l of the setback, wherein l is a maximum dimension of the setback in a longitudinal direction of the root of the blade, lies in a range of 10 to 35.

3. The blade according to claim 1 , wherein the platform includes at least one radially inner upstream portion defining at least one upstream bearing surface facing radially inwards, at least one of the fins defining a downstream bearing surface facing radially inwards such that a line passing via said upstream and downstream bearing surfaces is substantially perpendicular to a middle axis of the blade.

4. The blade according to claim 1 , wherein the platform has a main wall in the form of a portion of a finger or a portion of a cone that is extended upstream by a radial rim extending circumferentially, the rim being extended by a lip extending upstream.

5. The blade according to claim 4 , wherein the at least one rib extends downstream from the radial rim level with the upstream lip, said at least one rib including a radially inner surface defining said upstream bearing surface.

6. The blade according to claim 3 , wherein a main wall of the platform is extended downstream by a lip extending downstream.

7. The blade according to claim 3 , wherein the at least one rib extends radially inwards from a main wall of the platform level with the fins.

8. The blade according to claim 1 , wherein ends of the setback are rounded.

9. The blade according to claim 2 , wherein the maximum dimension of the setback in the longitudinal direction of the airfoil lies in a range of 14 mm to 20 mm, and the maximum dimension of the setback in the longitudinal direction of the root of the blade lies in a range of 0.7 mm to 1 mm.

10. The blade according to claim 1 , wherein a ratio L/l of a length L of the setback, wherein L is a maximum dimension of the setback in a longitudinal direction of the airfoil, divided by a width l of the setback, wherein l is a maximum dimension of the setback in a longitudinal direction of the root of the blade, lies in a range of 15 to 30.

11. The blade according to claim 10 , wherein the maximum dimension of the setback in the longitudinal direction of the airfoil lies in a range of 14 mm to 20 mm, and the maximum dimension of the setback in the longitudinal direction of the root of the blade lies in a range of 0.7 mm to 1 mm.

12. The blade according to claim 3 , wherein the upstream and downstream bearing surfaces are inclined relative to a plane perpendicular to the middle radial wall.

13. The blade according to claim 3 , wherein the upstream and downstream bearing surfaces are disposed relative to a plane perpendicular to the middle radial wall at an angle that lies in a range of 0 to 15°.

14. The blade according to claim 8 , wherein a radius of curvature of the ends lies in a range of 0.9 mm to 1.1 mm.

15. A turbine wheel for a turbine engine, the wheel comprising:
at least one of the blade according to claim 1 , and
the disk, which includes a radially outer periphery including a series of teeth defining slots of the disk between the teeth,
the root of the blade being engaged in the slot that is one of the slots of the disk in such a manner that the fins of the blade are bearable radially inwards against the two adjacent teeth of the disk, the root of the blade being spaced apart from a bottom of the slot.

Assignees

• Snecma

Inventors

• Dupeyre Raphael
• Alquier Damien
• Congratel Sebastien
• Klein Guillaume
• Mathieu David
• Tang Ba-Phuc
• Trahot Denis Gabriel

Classifications

• F01D11/006

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F01D5/30 Primary

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F01D11/008

  by spacer elements between the blades, e.g. independent interblade platforms · CPC title

• F01D5/3007

  of axial insertion type · CPC title