Nozzle stage for a turbomachine compressor
US8740553B2 · kind B2 · utility
0Cited by
2References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 30, 2010 |
| Grant date | Jun 3, 2014 |
| Priority date | — |
| Expiry date | Jul 13, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention relates to a nozzle stage for a turbomachine compressor, the stage comprising two coaxial shrouds, a radially inner shroud and a radially outer shroud, and radial vanes extending between the shrouds and being connected via their ends to the shrouds, together with a support for abradable material that is mounted by crimping onto the upstream and downstream edges of the inner shroud, the inner shroud presenting openings in which the radially inner ends of the vanes are inserted and fastened. The radially inner ends of the vanes are plane and do not have any projecting tenons.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.