Turbine blade comprising ribs between cooling outlets with cooling holes

Patent metadata

Field	Value
Publication number	US-11753945-B2
Application number	US-202117906300-A
Country	US
Kind code	B2
Filing date	Mar 9, 2021
Priority date	Mar 18, 2020
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

A turbomachine turbine blade, includes a platform, a vane, a cooling cavity supplying a plurality of cooling outlets provided along the trailing edge, two radially adjacent cooling outlets defining therebetween a rib. At least one cooling hole is formed in the thickness of at least one rib and/or in the thickness of a portion of the trailing edge fillet located in the axial extension of at least one rib, so as to ensure fluid communication for a cooling flow between the inside and the outside of the blade for cooling the at least one rib.

First claim

What is claimed is:

1. A turbomachine turbine blade, intended to be mounted around an axis of rotation, including a platform and a vane extending in a radial direction relative to the axis of rotation, going radially from the inside to the outside away from the platform and ending in a top, the vane comprising a leading edge and a trailing edge, the trailing edge being located downstream of the leading edge, and the vane comprising a lower surface wall and an upper surface wall each connecting the leading edge to the trailing edge, the lower surface wall and the upper surface wall being connected to each other at the trailing edge by a trailing edge fillet,
the blade including a cooling cavity supplying cooling flow to a plurality of cooling outlets emerging onto the trailing edge, the cooling outlets being provided along the trailing edge, on one of the lower surface and upper surface walls, between the platform and the top, two radially adjacent cooling outlets being delimited by a rib extending between an upstream end, located radially between the two radially adjacent cooling outlets, and a downstream end, which emerges onto the trailing edge,
wherein at least one cooling hole is formed in the thickness of at least one rib, between the upstream end and the downstream end, and/or in that at least one cooling hole, having a cylindrical portion, is formed in the thickness of a portion of the trailing edge fillet in the axial extension of at least one rib, downstream of the downstream end, so as to ensure fluid communication for a cooling flow between the inside and the outside of the blade for cooling said at least one rib.

2. The blade according to claim 1 , wherein said at least one cooling hole formed in the thickness of a portion of the trailing edge fillet ( 26 ) includes a drilling, the axis of said cooling hole being arranged in the extension of a median axis of said at least one rib, the median axis extending along the rib.

3. The blade according to claim 1 , wherein the cylindrical portion of said at least one cooling hole formed in the thickness of a portion of the trailing edge fillet has a diameter comprised between 0.10 mm and 0.50 mm.

4. The blade according to claim 3 , wherein said at least one cooling hole includes a groove which emerges onto the trailing edge and which flares out in the extension of the cylindrical portion of said at least one cooling hole.

5. The blade according to claim 4 , wherein the ratio between the radial dimension of said at least one cooling hole upstream of the groove and the diameter of the trailing edge fillet is strictly comprised within the range 0.25 and 0.85.

6. The blade according to claim 1 , wherein said at least one cooling hole formed in the thickness of at least one rib includes a drilling, having a cylindrical shape and/or with a first portion of cylindrical shape and a second portion of flared shape comprising divergent walls.

7. The blade according to claim 6 , wherein said cooling hole is cylindrical in shape with a ratio of the cross-sectional diameter to the radial dimension of the rib strictly comprised between 0.20 and 0.85, and/or wherein the ratio of the axial distance of said at least one cooling hole relative to the downstream end of the rib to the axial distance of the rib between its upstream and downstream ends is strictly comprised between 0.1 and 0.9.

8. The blade according to claim 1 , wherein it is a moving blade for a moving turbine wheel for a turbomachine.

9. A turbine for a turbomachine, including at least one moving wheel comprising a plurality of moving blades according to claim 1 , the turbine being a high pressure turbine.

10. A turbomachine, including at least one turbine according to claim 9 , the turbomachine being a twin-spool turbomachine.

Assignees

• Safran Aircraft Engines

Inventors

• Ostino Léandre
• Botrel Erwan Daniel

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2250/11

  triangular · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title