Turbomachine vane including an antivortex fin

Patent metadata

Field	Value
Publication number	US-10260361-B2
Application number	US-201514740405-A
Country	US
Kind code	B2
Filing date	Jun 16, 2015
Priority date	Jun 17, 2014
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

The invention relates to a turbomachine vane comprising a root and a blade including a median main plane having a longitudinal and radial main orientation, which is carried by the root, the blade including a leading edge located at an upstream longitudinal end, a trailing edge located at a longitudinal end downstream of the leading edge with respect to a gas stream flowing around the blade, a lower surface wall and an upper surface wall which are located laterally remote from each other and each connecting the leading edge to the trailing edge, and a top located at the free outer radial end of the blade, the blade further including a fin having a longitudinal main orientation which is carried by the lower surface side, which is located at the top of the blade, wherein the fin is radially inwardly offset with respect to the top of the blade.

First claim

The invention claimed is:

1. A turbomachine vane comprising a root and a blade including a median main plane having a longitudinal and radial main orientation, which is carried by the root,
the blade including a leading edge located at an upstream longitudinal end, a trailing edge located at a longitudinal end downstream of the leading edge with respect to a gas stream flowing around the blade, a lower surface wall and an upper surface wall which are located laterally remote from each other and each connecting the leading edge to the trailing edge, and a top located at the free outer radial end of the blade,
the blade further including a fin having a longitudinal main orientation which is carried by the lower surface wall, and which counteracts the formation of vortexes at the top of the blade, the fin including an upstream longitudinal end which is longitudinally offset downstream of the leading edge of the blade, a downstream longitudinal end which is longitudinally offset upstream of the trailing edge of the blade, and a lateral free end which is laterally offset a predetermined amount from the lower surface wall between the upstream longitudinal end and the downstream longitudinal end such that a shape of the lateral free end is similar to a shape of the lower surface wall,
the fin being radially inwardly offset with respect to the top of the blade, and
the top of the blade including a hollow recess which is radially outwardly open and including a bottom wall located radially remote from the top of the blade,
wherein the fin is radially inwardly offset with respect to the bottom wall of the recess,
wherein a connection between the lower surface wall and a radially inner face of the fin is convex-shaped,
wherein a longitudinal dimension of the fin is lower than a longitudinal dimension of the blade, and
wherein the fin includes a bore passing therethrough, a first end of the bore at the lateral free end of the fin and a second end of the bore in fluid communication with a cavity formed in the blade.

2. The turbomachine vane according to claim 1 , wherein a median longitudinal plane of the fin is perpendicular to the main plane of the blade.

3. The turbomachine vane according to claim 1 , wherein a median longitudinal plane of the fin is tilted relative to the main plane of the blade.

4. The turbomachine vane according to claim 1 , wherein the upstream longitudinal end of the fin is radially offset with respect to the downstream longitudinal end of the fin.

5. A turbomachine high pressure turbine rotor including a plurality of vanes according to claim 1 , which are regularly distributed about the main axis of rotation of the rotor.

6. The turbomachine vane according to claim 1 , wherein a median longitudinal plane of the fin is radially inwardly tilted with respect to a radial main axis of the vane.

7. The turbomachine vane according to claim 1 , wherein a median longitudinal plane of the fin is perpendicular to the main plane of the blade, or radially inwardly tilted with respect to a radial main axis of the vane.

8. The turbomachine vane according to claim 1 , wherein the connection between the lower surface wall and the radially inner face of the fin is laterally and radially inwardly bulged.

9. The turbomachine vane according to claim 1 , wherein the first end of the bore is radially inward of an inner surface of the bottom wall of the recess delimiting the cavity formed in the blade.

Assignees

• Safran Aircraft Engines

Inventors

• Botrel Erwan Daniel
• Coudert Laurent Patrick Robert

Classifications

• F05D2240/127

  Vortex generators, turbulators, or the like, for mixing · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title