Turbine vane comprising a passive system for reducing vortex phenomena in an air flow flowing over said vane

Patent metadata

Field	Value
Publication number	US-11473435-B2
Application number	US-201917251510-A
Country	US
Kind code	B2
Filing date	Jun 14, 2019
Priority date	Jun 15, 2018
Publication date	Oct 18, 2022
Grant date	Oct 18, 2022

Abstract

A vane for a turbine engine turbine includes a blade and at least one platform that radially extends the blade, and a system for reducing vortices including at least one circuit including a duct extending from at least one air intake orifice formed in the platform upstream of the leading edge as far as at least one air exhaust slot formed on the trailing edge.

First claim

The invention claimed is:

1. A turbine vane for a turbine engine, comprising:
a blade including a leading edge and a trailing edge and intended to be submerged in an air flow circulating from upstream to downstream from the leading edge to the trailing edge;
a platform ending an end of the blade, the platform comprising an air glide face at the interface thereof with the blade; and
an air circulation circuit including:
an air intake opening formed onto the glide face of the platform, in a zone upstream from the leading edge or in a zone corresponding to the upstream half of the blade;
an air discharge opening formed onto the trailing edge of the blade; and
an inner conduit connecting the air intake opening to the air discharge opening.

2. The vane according to claim 1 , wherein the inner conduit forms a coil including at least one undulation.

3. The vane according to claim 1 , wherein the air intake opening is an orifice, and the air discharge opening is a slit.

4. The vane according to claim 1 , wherein the inner conduit is configured to discharge air via the air discharge opening along a direction which is within 10° of a direction of a propagation of the air flow along the blade, downstream from the trailing edge.

5. The vane according to claim 1 , wherein the inner conduit connects a plurality of air intake openings to an air discharge opening.

6. The vane according to claim 1 , wherein the inner conduit connects an air intake opening to a plurality of air discharge openings.

7. The vane according to claim 1 , comprising a radially internal platform and a radially external platform, and comprising a first air circulation circuit at the level of the radially internal platform, and a second air circulation circuit at the level of the radially external platform.

8. The vane according to claim 1 , obtained by additive manufacturing.

9. A turbine for an aircraft turbine engine comprising at least one vane according to claim 1 .

10. An aircraft turbine engine comprising at least one turbine according to claim 9 .

11. The turbine according to claim 9 , wherein the turbine is a low-pressure turbine.

12. The aircraft turbine engine according to claim 10 , wherein the turbine engine is a double-body turbine engine.

13. The vane according to claim 1 , wherein the inner conduit includes a first curvature, of concave shape viewed from an opposite platform located on an end of the blade opposite to the platform, extending radially toward the blade until the inner conduit traverses the guide face, and a second curvature of convex shape viewed from the opposite platform, the second curvature configured to rectify air discharged from the air discharge opening along a direction of a propagation of the air flow along the blade.

Assignees

• Safran Aircraft Engines

Inventors

• Pintat Ludovic
• Schwartz Eric Roger

Classifications

• F01D5/145

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• F05D2240/81

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• F05D2220/323

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• F05D2270/17

  to control boundary layer · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title