Mobile turbine blade with an improved design for an aircraft turbomachine

Patent metadata

Field	Value
Publication number	US-2016281525-A1
Application number	US-201615081079-A
Country	US
Kind code	A1
Filing date	Mar 25, 2016
Priority date	Mar 27, 2015
Publication date	Sep 29, 2016
Grant date	—

Abstract

A turbine blade for an aircraft turbomachine including a root, an airfoil and a platform inserted between the airfoil and the root and delimiting a gas circulation flowpath, the platform having two axial ends each forming an angel wing of which at least one has an internal cavity that will be supplied with air from the root of the blade. At least one of the two angel wings is drilled with at least one bleed hole for passage of a bleed flow from the internal cavity that will limit/prevent gas recirculation outside the flowpath.

First claim

1 . A turbine blade for an aircraft turbomachine comprising a root, an airfoil and a platform inserted between the airfoil and the root and delimiting a gas circulation flowpath, the platform having two axial ends each forming an angel wing of which at least one has an internal cavity that will be supplied with air from the root of the blade,
wherein at least one of the two angel wings is drilled with at least one bleed hole for passage of a bleed flow from the internal cavity that will limit/prevent gas recirculation outside said flowpath by bypassing said angel wing, and wherein the blade comprises a stiffener associated with each of the two angel wings, each stiffener extending radially inwards from its associated angel wing, along a circumferential length approximately equal to the length of the angel wing, and in that said cavity of at least one of the two angel wings also extends along part of its associated stiffener.

2 . The blade according to claim 1 , wherein said internal cavity of the angel wing extends along a circumferential length corresponding to at least 75% of the circumferential length of the angel wing.

3 . The blade according to claim 1 , wherein it comprises a shank radially connecting the root of the blade and the platform, the two angel wings each projecting circumferentially on each side of the shank, and in that said cavity of at least one of the two angel wings also extends into part of said shank.

4 . The blade according to claim 1 , wherein each angel wing comprises a radially outer surface, a radially inner surface, and a junction edge between the radially inner surface and the radially outer surface, and in that said at least bleed hole passes through said junction edge.

5 . The blade according to claim 1 , wherein each bleed hole is oriented approximately along the axial direction or is inclined radially outwards from the axial direction, by an angle Aa between −10° and 10°.

6 . An assembly comprising a turbine blade according to claim 1 and a nozzle segment arranged axially facing said blade, said nozzle segment comprising an airfoil and a platform also delimiting the gas circulation flowpath, the platform of the nozzle segment comprising an axial end in the form of an angel wing, axially facing one of the two angel wings of the turbine blade provided with said at least one bleed hole, and in that said at least one bleed hole carries a bleed flow originating from the internal cavity and that will limit/prevent recirculation of gas outside said flowpath ( 14 a ) by passing between the two facing angel wings ( 46 , 90 ).

7 . The turbine wheel for an aircraft turbomachine comprising a disk and a plurality of blades according to claim 1 , each turbine blade being mounted on the disk.

8 . The aircraft turbomachine comprising at least one turbine blade according to claim 1 .

9 . A method of manufacturing a turbine blade according to claim 1 , wherein each angel wing cavity is achieved by eliminating a wax block after casting the blade in a mould, and in that each bleed hole is then made by machining the angel wing.

Assignees

• Snecma

Inventors

• Nguyen David Thien-Roger
• Boisnault Franck
• Judet Maurice Guy
• Person Laetitia

Classifications

• F01D11/02 Primary

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D11/04

  using sealing fluid, e.g. steam · CPC title