ANTI-WEAR DEVICE FOR THE BLADES OF A TURBINE DISTRIBUTOR IN AN AERONAUTICAL TURBINE ENGINE

• US 20120128481A1
• Filed: 11/25/2009
• Published: 05/24/2012
• Est. Priority Date: 11/26/2008
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Durand, Didier Noel, Herzer, Eric, Baumas, Olivier,Jean Daniel, Rossi, Patrick Jacques
• Granted Patent: US 9,062,553 B2
• Time in Patent Office: Days
• US Class Current: 415/209.2
• CPC Class Codes: F01D 5/3092 Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers F01D5/288 takes precedence
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F05D 2300/509 Self lubricating materials; Solid lubricants
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A blade sector of a turbine distributor to be carried by a turbine casing of an aeronautical turbine engine, including a front connection mechanism and a rear connection mechanism, wherein the front connection mechanism is adapted so as to bear against a holder carried by the turbine casing. The sector further includes an anti-wear device formed by a piece of a metal material surrounding the front end of the front connection mechanism and provided between the front connection mechanism and the holder to ensure a sliding contact between the two parts. The anti-wear device is axially maintained in position on the blade sector using an attachment mechanism engaging with the front connection mechanism.

Claims

1-14. -14. (canceled)

15. :

A turbine distributor blade segment configured to be supported by a turbine casing of an aeronautical turbo-engine, comprising;

a front connection means and a rear connection means, the front connection means configured to rest on a support which is supported by the turbine casing;

an anti-wear device including a part made of metal material that envelops a front end of the front connection means, and is interposed between the front connection means and the support, to provide sliding contact between the front connection means and the support,

wherein the anti-wear device is retained axially in position on the blade segment by a securing means that co-operates with the front connection means.

16. :

The blade segment as claimed in claim 15, wherein the front connection means is in a form of a tongue that extends axially, and an upper part of the device does not extend axially along an entire length of the front connection means.

17. :

The blade segment as claimed in claim 15, wherein the anti-wear device is retained in place on a front connection means by at least one pin that is fitted into a bore provided in a thickness of the connection means.

18. :

The blade segment as claimed in claim 15, wherein the anti-wear device extends along an entire length of the front connection means, and is prolonged at its rear end by a projection, the front connection means having a form of a tongue that extends axially, and comprising at its rear end a groove in which the projection is engaged.

19. :

The blade segment as claimed in claim 15, wherein the anti-wear device comprises at least one tab that extends along an entire length of the front connection means, and ends in a projection at its rear end, the front connection means having a form of a tongue that extends axially, and comprising at its rear end a groove in which the projection is engaged.

20. :

The blade segment as claimed in claim 19, wherein an overall thickness of the anti-wear device, measured radially, is smaller than or equal to that of the tongue increased by that of the part of the device which is situated between the front connection means and the support, such that the device does not project above the upper part of the tongue, the tongue having set-backs that make it possible to insert the tabs into them.

21. :

The blade segment as claimed in claim 15, wherein the anti-wear device extends along an entire length of the front connection means, and comprises at its rear end at least one dropped edge, the front connection means having a form of a tongue which extends axially, and comprising at its rear end at least one cut-out which can receive the dropped edge.

22. :

The blade segment as claimed in claim 15, wherein the anti-wear device extends along an entire length of the front connection means, and comprises on its upper surface at least one indentation, the front connection means having a form of a tongue that extends axially, and comprising on an upper part of the tongue at least one indentation that can co-operate with the indentation in the device.

23. :

The blade segment as claimed in claim 15, in which the anti-wear device has a length along a circumference that is substantially equal to that of the segment, and is positioned with angular offsetting relative to the segment, to overlap an adjacent segment at least partially and to provide sealing between the two segments.

24. :

The blade segment as claimed in claim 15, wherein the anti-wear device is made of a superalloy based on nickel or cobalt.

25. :

The blade segment as claimed in claim 24, wherein the metal material is an alloy which is sold under name HA188.

26. :

The blade segment as claimed in claim 15, wherein a thickness of the material of the anti-wear device is between 0.05 and 0.4 mm.

27. :

A turbine module of an aeronautical turbo-engine comprising at least one distributor-blade wheel including segments as claimed in claim 15.

28. :

An aeronautical engine comprising at least one turbine module as claimed in claim 27.