초록 ▼

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 sec

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.

대표청구항 ▼

1. A turbine distributor blade segment configured to be supported by a turbine casing of an aeronautical turbo-engine, comprising: a front connection structure of the turbine distributor blade segment and a rear connection structure of the turbine distributor blade segment, the front connection stru

1. A turbine distributor blade segment configured to be supported by a turbine casing of an aeronautical turbo-engine, comprising: a front connection structure of the turbine distributor blade segment and a rear connection structure of the turbine distributor blade segment, the front connection structure configured to rest on a support which is supported by the turbine casing; andan anti-wear device including a part made of metal material that envelops a front end of the front connection structure, and is interposed between the front connection structure and the support, to provide sliding contact between the front connection structure and the support,wherein the anti-wear device is retained axially in position on the blade segment by a securing structure that co-operates with the front connection structure, andwherein the anti-wear device extends along an entire length of the front connection structure, and includes at a rear end of the anti-wear device at least one dropped edge, the front connection structure including a form of a tongue which extends axially, and including at a rear end of the front connection structure at least one cut-out which can receive the dropped edge. 2. The blade segment as claimed in claim 1, 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. 3. The blade segment as claimed in claim 1, wherein the anti-wear device is made of a superalloy based on nickel or cobalt. 4. The blade segment as claimed in claim 3, wherein the metal material is an alloy which is sold under name HA188. 5. The blade segment as claimed in claim 1, wherein a thickness of the material of the anti-wear device is between 0.05 and 0.4 mm. 6. A turbine module of an aeronautical turbo-engine comprising at least one distributor-blade wheel including segments as claimed in claim 1. 7. An aeronautical engine comprising at least one turbine module as claimed in claim 6. 8. The blade segment as claimed in claim 1, wherein at least a portion of the anti-wear device is sandwiched between the front connection structure and a thermal insulation. 9. The blade segment as claimed in claim 1, wherein at least a portion of the front connection structure or of the anti-wear device supports a fire-protection plate. 10. The blade segment as claimed in claim 1, wherein the anti-wear device straddles a plurality of turbine distributor blade segments. 11. A turbine distributor blade segment configured to be supported by a turbine casing of an aeronautical turbo-engine, comprising: a front connection structure and a rear connection structure, the front connection structure 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 structure, and is interposed between the front connection structure and the support, to provide sliding contact between the front connection structure and the support,wherein the anti-wear device is retained axially in position on the blade segment by a securing structure that co-operates with the front connection structure,wherein the anti-wear device comprises at least one tab that extends along an entire length of the front connection structure, and ends in a projection at its rear end, the front connection structure having a form of a tongue that extends axially, and comprising at its rear end a groove in which the projection is engaged, andwherein 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 structure 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 at least one tab into them.