Method for modifying gas turbine nozzle area
US7186070B2 · kind B2 · utility
6Cited by
10References
38Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 12, 2004 |
| Grant date | Mar 6, 2007 |
| Priority date | — |
| Expiry date | Mar 4, 2025 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of modifying a turbine nozzle area comprises depositing a thermal barrier coating (TBC) on the nozzle endwalls to provide a minimum nozzle area, evaluating an airflow through the nozzle, and machining the TBC to increase the nozzle area. Adjacent segment area variation may be minimized, improving engine reliability by reducing the aerodynamic excitation to the down stream blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.