Turbine engine compressor, in particular of an aeroplane turboprop or turbofan

Patent metadata

Field	Value
Publication number	US-2016348530-A1
Application number	US-201415103956-A
Country	US
Kind code	A1
Filing date	Dec 4, 2014
Priority date	Dec 19, 2013
Publication date	Dec 1, 2016
Grant date	—

Abstract

The invention relates to a turbine engine compressor, in particular of an aeroplane turboprop or turbofan, comprising a stator featuring an annular casing and at least one annular row of variable-pitch vanes, wherein each vane comprises a radially external end having a pivot mounted in an orifice in the casing and connected by a linking member to an control ring ( 38 ) capable of pivoting axially in relation to the casing, wherein said linking member comprises a first end fixed to the pivot of the vane and a second end having a pin inserted in a hole ( 52, 58 ) in the control ring ( 38 ), characterised in that one ( 58 ) at least of the holes ( 52, 58 ) in the control ring ( 38 ) serving for insertion of the pins of the linking members, is oblong in shape and extends in the circumferential direction in order to allow movement of the pin in said oblong hole ( 58 ), during rotation of the control ring ( 38 ).

First claim

1 . Turbine engine compressor, in particular of an aeroplane turboprop or turbofan, comprising a stator featuring an annular casing and at least one annular row of variable-pitch vanes, wherein each vane comprises a radially external end having a pivot mounted in an orifice in the casing and connected by a linking member to an control ring capable of pivoting axially in relation to the casing, wherein said linking member comprises a first end fixed to the pivot of the vane and a second end having a pin inserted in a hole in the control ring, wherein the control ring comprises at least one cylindrical hole, into which a cylindrical pin of a linking member is inserted, wherein the diameters of the cylindrical pin and of the hole are substantially identical and at least one oblong hole extending circumferentially, into which another cylindrical pin of another linking member is inserted in order to allow movement of said pin in said oblong hole, during rotation of the control ring.

2 . Compressor according to claim 1 , wherein the pins are cylindrical.

3 . Compressor according to claim 1 , wherein one at least of the holes in the control ring, serving for insertion of the pins of the linking members, is shaped so as to inhibit movement of the pin in said hole.

4 . Compressor according to claim 1 , wherein said oblong hole in the control ring comprises a first end located on the side of a first lateral edge of the control ring and a second end located on the side of a second lateral edge of the control ring, wherein both ends are connected by a curved joining area featuring an inflection point.

5 . Compressor according to claim 1 , wherein said oblong hole in the control ring extends solely in the circumferential direction.

6 . Compressor according to claim 1 , wherein said oblong hole in the control ring extends obliquely in relation to the axial direction and in relation to the circumferential direction.

7 . Compressor according to claim 1 , wherein said oblong hole in the control ring forms an arc shape.

8 . Compressor according to claim 1 , wherein said oblong hole in the control ring comprises a first end extending solely circumferentially and located on the side of a first lateral edge of the control ring and a second end extending solely circumferentially located on the side of the other lateral edge of the control ring, wherein said ends are connected by a joining area extending obliquely in relation to the circumferential direction and in relation to the axial direction.

9 . Turbine engine, such as for example an aeroplane turboprop or a turbofan, comprising at least one compressor according to claim 1 .

Assignees

• Snecma
• Scnema

Inventors

• Sebrecht Pierre-Alainx Francis Claude
• Cochon Sébastien
• Langlois Arnaud

Classifications

• F01D17/167

  of vanes moving in translation · CPC title

• F01D17/162 Primary

  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

• F04D29/56

  adjustable · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F05D2270/58

  by mechanical means, e.g. levers, gears or cams · CPC title