Turbine engine blade with improved cooling

Patent metadata

Field	Value
Publication number	US-11946387-B2
Application number	US-202017617981-A
Country	US
Kind code	B2
Filing date	Jun 11, 2020
Priority date	Jun 13, 2019
Publication date	Apr 2, 2024
Grant date	Apr 2, 2024

Abstract

A turbine blade, including a root, a vane including a leading edge and a trailing edge and a pressure-side wall and a suction-side wall, and including cooling vents at the trailing edge, this vane also including first and second serpentine circuits; each serpentine circuit including several ducts extending in the span direction, being connected to each other by angled portions; each serpentine circuit being supplied with air by its duct that is closest to the leading edge; and wherein the vents are supplied by the first and by the second serpentine circuit.

First claim

The invention claimed is:

1. A turbine vane of a turbomachine, comprising:
a root carrying a blade extending along a span direction, said blade comprising a trailing edge provided with cooling vents, a first serpentine circuit, and a second serpentine circuit, wherein:
each serpentine circuit includes several ducts extending along the span direction by being connected to each other through bent portions;
each serpentine circuit is supplied with air by a mouth located at the root via its duct which is furthest from the trailing edge;
the first serpentine circuit has an even number of ducts and the second serpentine circuit has an odd number of ducts, or vice versa,
the first serpentine circuit and the second serpentine circuit are terminated by a first terminal duct and a second terminal duct respectively, the first and second terminal ducts running along the trailing edge as an extension of each other, and by being separated from each other by an inner partition wall of the blade, and
the vents are supplied with cooling air from the first serpentine circuit and from the second serpentine circuit.

2. The vane according to claim 1 , wherein the first serpentine circuit supplies the vents closest to the root with air, and wherein the second serpentine circuit supplies the other vents with air.

3. The vane according to claim 1 , wherein the second serpentine circuit supplies the vents closest to an apex part of the blade with air, and wherein the first serpentine circuit supplies the other vents with air.

4. The vane according to claim 1 , wherein the first serpentine circuit includes a first upstream duct, a first middle duct, and a first terminal duct, and wherein the second serpentine circuit includes a second upstream duct, a second middle duct, a second downstream duct, and a second terminal duct, and wherein these ducts are elongate.

5. The vane according to claim 1 , wherein the ducts of the first serpentine circuit extend on a lower surface side by running along a lower surface wall of the blade, and wherein the ducts of the second serpentine circuit extend on an upper surface side by miming along an upper surface wall of the blade.

6. The vane according to claim 1 , wherein the vane includes a lower surface wall including cooling holes supplied with air from the first serpentine circuit.

7. The vane according to claim 1 , comprising a leading edge and an upstream circuit dedicated to cooling said leading edge.

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

9. The vane according to claim 1 , made of composite or ceramic material.

10. A turbine comprising a vane according to claim 1 .

11. An aircraft turbomachine comprising a turbine according to the claim 10 .

Assignees

• Safran Aircraft Engines

Inventors

• Botrel Erwan Daniel
• Garles Kevin Yannick
• Coudert Laurent Patrick Robert

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F01D5/30

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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title