Variable pitch rectifier for a turbomachine compressor comprising two inner rings

Patent metadata

Field	Value
Publication number	US-10385872-B2
Application number	US-201314389889-A
Country	US
Kind code	B2
Filing date	Mar 28, 2013
Priority date	Apr 3, 2012
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A variable pitch rectifier for a compressor includes a plurality of radial vanes having respectively, at outer and inner ends of same, outer and inner pivots, the inner pivots being received between two upstream and downstream inner rings, which are assembled by a link device. The link device includes only a set of angular sectors of elastically deformable stirrups, arranged to grip together the inner peripheral edges of the upstream and downstream rings by clamping one against the other.

First claim

The invention claimed is:

1. A variable pitch rectifier for a compressor, comprising:
a plurality of radial vanes including outer and inner pivots at outer and inner ends of the vanes, respectively, each of the inner pivots being received, with regard to a gas flow circulating in an upstream to downstream direction of said compressor, between two upstream and downstream inner back-to-back rings that are coaxial to an axis parallel to the upstream to downstream direction and that are fixed together back-to-back in the upstream to downstream direction via a connection device,
wherein the connection device for connecting the inner back-to-back rings to each other comprises angular sectors of elastically deformable sectored stirrups arranged to grip inner peripheral edges of the upstream and downstream rings by firmly clipping upstream and downstream facing surfaces of the inner back-to-back rings so as to firmly clip the inner back-to-back rings to each other, at least in the upstream to downstream direction, wherein each stirrup comprises opposing wings projecting towards an inside of each stirrup, the wings engaging an upstream facing surface within a transverse notch provided on the upstream facing surface of the upstream ring and a downstream facing surface within a transverse notch provided on the downstream facing surface of the downstream ring.

2. The rectifier according to claim 1 , wherein the sectored stirrups have a cross section that is substantially U-shaped or of similar shape.

3. The rectifier according to either claim 1 , wherein the sectored stirrups comprise a holding means for holding the clipped inner back-to-back rings.

4. The rectifier according to claim 1 , wherein a support for receiving an abradable material is associated with each of the sectored stirrups.

5. The rectifier according to claim 4 , wherein each support is fixed by being welded to an outside of a bottom of the corresponding sectored stirrup and extends along the bottom of each stirrup to receive the abradable material.

6. The rectifier according to claim 1 , wherein the sectored stirrups are rotationally immobilized relative to the assembled inner back-to-back rings.

7. The rectifier according to claim 6 , wherein rotation stop studs laterally project from respective upstream and downstream transverse faces of the assembled inner back-to-back rings and, between two consecutive studs, transverse end faces of a stirrup are engaged.

8. The rectifier according to claim 1 , wherein transverse end faces of the stirrups are stepped so that a stepped face of a stirrup cooperates with a complementary stepped face of an adjacent stirrup.

9. The turbine engine compressor comprising an alternating succession of wheels forming rotors and of rectifiers forming a stator, and variable pitch rectifiers according to claim 1 .

10. The rectifier according to claim 1 , wherein the connection device connects inner back-to-back 360° rings.

11. A variable pitch rectifier for a compressor, comprising:
a plurality of radial vanes including outer and inner pivots at outer and inner ends of the vanes, respectively, each of the inner pivots being received by a bush, the bushes being received between cylindrical half-housings of upstream and downstream rings that are assembled via a connection device,
wherein the connection device for connecting the rings comprises only one set of angular sectors of elastically deformable stirrups arranged to grip inner peripheral edges of the upstream and downstream rings by clipping the inner peripheral edges of the upstream and downstream rings together, each of the stirrups having a substantially U-shaped cross section with lateral and opposing wings,
wherein each of the wings includes an inner ledge respectively projecting towards an inside of each stirrup, the inner ledges engaging an upstream facing surface within a transverse notch provided on an upstream facing surface of the upstream ring and a downstream facing surface within a transverse notch provided on a downstream facing surface of the downstream ring, and
wherein a bottom of at least one of the stirrups abuts a radially inner end of at least one of the bushes and the inner peripheral edges of the upstream and downstream rings.

12. A variable pitch rectifier for a compressor, comprising:
a plurality of radial vanes including outer and inner pivots at their outer and inner ends respectively, each of the inner pivots being received, with regard to a gas flow circulating in an upstream to a downstream direction of said compressor, between two upstream and downstream inner back-to-back rings that are coaxial to an axis parallel to the upstream to downstream direction and that are fixed together back-to-back in the upstream to a downstream direction via a connection device,
wherein said connection device for connecting said inner back-to-back rings to each other comprises angular sectors of elastically deformable sectored stirrups arranged to grip inner peripheral edges of the upstream and downstream rings by firmly clipping said inner back-to-back rings to each other, at least in the upstream to downstream direction, and
wherein each stirrup comprises opposing wings projecting towards an inside of each stirrup, the wings engaging an upstream facing surface within a transverse notch provided on the upstream facing surface of the upstream ring and a downstream facing surface within a transverse notch provided on the downstream facing surface of the downstream ring.

Assignees

• Safran Aircraft Engines

Inventors

• Hugon Nadege
• Bart Jacques Rene

Classifications

• F05D2300/501

  Elasticity · CPC title

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title

• F04D29/563 Primary

  specially adapted for elastic fluid pumps · CPC title