Mobile turbine blade with an improved design for an aircraft turbomachine

Patent metadata

Field	Value
Publication number	US-10526906-B2
Application number	US-201615081079-A
Country	US
Kind code	B2
Filing date	Mar 25, 2016
Priority date	Mar 27, 2015
Publication date	Jan 7, 2020
Grant date	Jan 7, 2020

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

The invention claimed is:

1. A turbine blade for an aircraft turbomachine wherein the turbine blade is mounted for rotation about a rotation axis, the turbine blade comprising a root having at least one cooling air duct extending radially relative to the rotation axis, 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 by the at least one radially extending cooling air duct, wherein the at least one internal cavity has a sectional area in a plane including the rotation axis direction greater than that of any one of the at least one radially extending cooling air ducts,
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 inhibit gas recirculation outside said flowpath by bypassing said at least one of the two angel wings, and
wherein the blade comprises a stiffener extending radially inwards from each of the two angel wings, each said stiffener having a circumferential length equal to a circumferential length of the respective angel wing, and wherein said cavity of the at least one of the two angel wings extends in axial alignment with a respective one of said stiffeners and in a radial direction along part of the respective one of said stiffeners to a location radially inwards from said at least one of the two angel wings.

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

3. The blade according to claim 1 , further comprising a shank radially connecting the root of the blade and the platform and having sides in a circumferential direction, the two angel wings each projecting circumferentially on each side of the shank, wherein said cavity of the 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, wherein said at least one bleed hole of the at least one of said two angel wings passes through the junction edge of the respective angel wing.

5. The blade according to claim 1 , wherein each bleed hole is oriented along an 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 the at least one of the two angel wings of the turbine blade provided with said at least one bleed hole, wherein said at least one bleed hole carries the bleed flow originating from the internal cavity, which bleed flow will inhibit recirculation of gas outside said flowpath by passing between the two facing angel wings.

7. A 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. An aircraft turbomachine comprising at least one turbine blade according to claim 1 .

9. A method of manufacturing the 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 wherein 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

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D11/04

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

• F05D2220/32

  in gas turbines · CPC title

• 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

• F01D5/187 Primary

  Convection cooling · CPC title