Turbine stator for aircraft turbine engine including a vibration damping device
US8133010B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 8, 2008 |
| Grant date | Mar 13, 2012 |
| Priority date | — |
| Expiry date | Nov 7, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine stator for an aircraft turbine engine is disclosed. The turbine stator includes a stator wall supporting a high pressure air injector fixed on the downstream side, and an annular abradable element support. The lower radial end of the element support is fixed to the high pressure air injector and the upper radial end of the element support is fixed to the stator wall, such that they jointly delimit a cavity under pressure. The turbine stator also includes at least one vibration damping device located in the cavity under pressure. The vibration damping device is in contact with each of the two elements taken among the stator wall and the annular support.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.