Methods and apparatus for reducing nozzle stress
US8096757B2 · kind B2 · utility
4Cited by
7References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 2, 2009 |
| Grant date | Jan 17, 2012 |
| Priority date | — |
| Expiry date | Jun 12, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine nozzle is described. The gas turbine engine nozzle includes at least one nozzle vane having a first end and a second end. The first end is coupled to an inner sidewall and the second end is coupled to an outer sidewall. The gas turbine engine nozzle also includes at least one stress relief pocket defined within at least one of the inner sidewall and the outer sidewall proximate to the at least one nozzle vane. The at least one stress relief pocket is configured to reduce stress on the proximate nozzle vane.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.