Compressor casing comprising cavities having an optimised upstream shape

Patent metadata

Field	Value
Publication number	US-9638213-B2
Application number	US-201314391080-A
Country	US
Kind code	B2
Filing date	Apr 15, 2013
Priority date	Apr 19, 2012
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

A casing for a turbine engine compressor, including: cavities in a thickness of the casing, extending in parallel to one another from an inner face of the casing along a circumference thereof, the cavities not being in communication with one another. The cavities, which are elongate and extend along a main direction of orientation between two side walls, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the inner face of the casing. The upstream border of the cavities takes a form of a wavy line including at least two alternate undulations over a length thereof between the side walls.

First claim

The invention claimed is:

1. A casing for a turbine engine compressor comprising:
cavities hollowed out, so as not to communicate with one another, in a thickness of the casing from its internal face and disposed parallel to one another on a circumference of the casing, the cavities having an elongate form in a principal orientation direction between two lateral walls and being closed towards an upstream end and towards a downstream end by an upstream face and by a downstream face respectively, intersections of which with the internal face of the casing form an upstream boundary and a downstream boundary respectively,
wherein the upstream boundary of these cavities is in a form of an undulating line comprising at least two half-waves on its length lying between the lateral walls.

2. A casing for a compressor according to claim 1 , wherein the lateral walls converge towards each other while being directed from downstream to upstream.

3. A casing for a compressor according to claim 1 , wherein the undulating line is a broken zigzag line, of segments forming with one another alternately projecting angles and re-entrant angles.

4. A casing for a compressor according to claim 1 , wherein the upstream face of the cavities is formed by a succession of teeth extending, radially, between the upstream boundary and a bottom of the cavity and, axially, alternately towards the upstream end and towards the downstream end of the cavity.

5. A casing for a compressor according to claim 1 , wherein the downstream face has a convex shape.

6. A casing for a compressor according to claim 1 , wherein the cavities are distributed evenly over a circumference of the casing.

7. A casing for a compressor according to claim 1 , wherein the cavities are distributed unevenly over a circumference of the casing.

8. A compressor for a turbine engine comprising a casing according to claim 1 .

9. A turbine engine comprising a compressor according to claim 8 .

Assignees

• Snecma

Inventors

• Obrecht Thierry Jean-Jacques
• Domercq Olivier Stephane

Classifications

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F04D29/547 Primary

  having a special shape in order to influence fluid flow · CPC title

• F04D29/164

  of an axial flow wheel · CPC title

• F04D29/4206

  especially adapted for elastic fluid pumps · CPC title

• F04D29/541

  Specially adapted for elastic fluid pumps (F04D29/56 takes precedence) · CPC title