Guide device for variable pitch stator vanes of a turbine engine, and a method of assembling such a device

Patent metadata

Field	Value
Publication number	US-10280941-B2
Application number	US-201415100205-A
Country	US
Kind code	B2
Filing date	Nov 19, 2014
Priority date	Nov 29, 2013
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical bushings, each being put into place in a chimney of the inner ring from the inside and each serving to receive a guide pivot of a stator vane, a plurality of reconstitution ring angular sectors arranged end-to-end in order to form a reconstitution ring and put into place radially from the inside against the inner ring, and a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble the rings together.

First claim

The invention claimed is:

1. A device for guiding variable pitch stator vanes of a turbine engine, the device comprising:
a plurality of inner ring angular sectors arranged end-to-end in a circumferential direction in order to form an inner ring, each inner ring angular sector having chimneys passing radially through the inner ring sector;
a plurality of cylindrical bushings, each cylindrical bushing being put into place in a chimney of the inner ring from an inside and each cylindrical bushing serving to receive a guide pivot of a stator vane;
a plurality of reconstitution ring angular sectors arranged end-to-end in the circumferential direction order to form a reconstitution ring and put into place radially from an inside against the inner ring; and
a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble said rings together,
wherein each reconstitution ring angular sector presents a channel section with an inner portion forming a web and two side edges extending radially outwards, and
wherein each inner ring angular sector includes an inner face that is radially opposite from an outer face, and two side faces, the channel section of each reconstitution ring angular sector radially receiving the two side faces and the inner face of one of the inner ring angular sectors.

2. A device according to claim 1 , wherein each side edge of each reconstitution ring annular sector presents orifices for passing a blocking element.

3. A device according to claim 1 , wherein the reconstitution ring angular sectors are put into place against the inner ring in such a manner as to cover inter-sector zones of the inner ring.

4. A device according to claim 1 , wherein each inner ring angular sector presents a hole that is angularly positioned between two adjacent chimneys and that passes axially right through the inner ring angular sector in order to pass a blocking element.

5. A device according to claim 1 , wherein each blocking element comprises a bolt that is tightened in a crimped nut.

6. A device according to claim 1 , wherein each reconstitution ring angular sector carries on an inside face thereof a support for an abradable coating for co-operating with wipers carried by a rotor.

7. A turbine engine compressor including at least one device according to claim 1 .

8. A turbine engine including a compressor according to claim 7 .

9. The device according to claim 1 , wherein each reconstitution ring angular sector includes a downstream portion extending downstream from a radially outer end of a downstream side edge.

10. The device according to claim 1 , wherein the web of the reconstitution ring angular sectors abuts the inner face of the inner ring angular sectors.

11. A method of assembling a guide device for variable pitch stator vanes in a turbine engine according to claim 1 , the method comprising in succession:
inserting control pivots for stator vanes through a single-piece casing shell;
putting a set of inner ring angular sectors into place radially while inserting the guide pivots of the stator vanes in the chimneys of said inner ring angular sectors;
inserting bushings from the inside into the inner ring angular sector chimneys in order to take up a clearance that exists between the chimneys and the guide pivots of the stator vanes so as to enable the inner ring angular sectors to be put into place;
assembling the reconstitution ring angular sectors radially from the inside against the inner ring angular sectors; and
inserting the blocking elements in the inner ring angular sectors and the reconstitution ring angular sectors in order to assemble the inner and reconstitution rings together.

Assignees

• Safran Aircraft Engines

Inventors

• Mouton Clementine Charlotte Marie
• Belmonte Olivier

Classifications

• 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

• F04D29/642

  by adjusting the clearances between rotary and stationary parts · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title

• F04D29/563 Primary

  specially adapted for elastic fluid pumps · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic