SECTOR OF A COMPRESSOR GUIDE VANES ASSEMBLY OR A SECTOR OF A TURBOMACHINE NOZZLE ASSEMBLY

• US 20070297900A1
• Filed: 06/15/2007
• Published: 12/27/2007
• Est. Priority Date: 06/23/2006
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: LOMBARD, Jean-Pierre Francois, GARCIN, Francois Maurice, DEZOUCHE, Laurent Gilles, ABGRALL, Olivier
• Granted Patent: US 7,887,286 B2
• Time in Patent Office: Days
• US Class Current: 415/209.3
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A sector of a compressor guide vanes assembly or a sector of a turbomachine nozzle assembly. It comprises an inner ring sector (4), an outer ring sector (6) and a multitude of blades (8) connecting the inner ring sector (4) to the outer ring sector (6). The outer ring sector (6) or the inner ring sector (4) comprises radial cuts (10) situated between two consecutive blades (8) in such a way as to split them into the same number of elementary sectors as there are blades. Housings (14) are provided, secant to the radial cuts (10), damping inserts (16) being positioned in said housings.

Claims

1. A sector of a compressor guide vanes assembly or a sector of a turbomachine nozzle assembly comprising an inner ring sector, an outer ring sector and a multitude of blades connecting the inner ring sector to the outer ring sector, the outer ring sector or the inner ring sector comprising radial cuts situated between two consecutive blades in such a way as to split them into the same number of elementary sectors as there are blades, wherein:

housings are provided, secant to the radial cuts, damping inserts being positioned in said housings; and

the inserts consist of at least one viscoelastic layer, each viscoelastic layer being sandwiched between two metal layers.

2. The sector as claimed in claim 1, wherein the damping inserts are fitted into said housings such that they are free.

3. The sector as claimed in claim 1, wherein the damping inserts are fitted into said housings such that they are preloaded.

4. The sector as claimed in one of claims 1 to 3, wherein the housings are perpendicular to the radial cuts.

5. The sector as claimed in claim 2, wherein the damping inserts have an H-shaped geometry.

6. The sector as claimed in claim 2, wherein the inserts have an X-shaped geometry.

7. The sector as claimed in claim 3, wherein the damping inserts have a hairpin-shaped geometry.

8. The sector as claimed in claim 3, wherein the damping inserts have a wavy geometry.

9. The sector as claimed in claim 3, wherein the damping inserts have a U-shaped geometry.

10. The sector as claimed in claim 3, wherein the damping inserts have a Z-shaped geometry.

11. The sector as claimed in claim 3, wherein the damping inserts have an S-shaped geometry.

12. A turbomachine compressor which is equipped with at least one sector as claimed in one of claims 1 to 11.

13. A turbomachine turbine which is equipped with at least one sector as claimed in one of claims 1 to 11.

14. A turbomachine which comprises a compressor as claimed in claim 12 and/or a turbine as claimed in claim 13.