Gas turbine engine turbine nozzle impingement cover
US9371735B2 · kind B2 · utility
0Cited by
5References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 29, 2012 |
| Grant date | Jun 21, 2016 |
| Priority date | — |
| Expiry date | Feb 11, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/232
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An impingement cover (460) for fusing to a gas turbine engine turbine nozzle (451) with a nozzle rail (455) includes a body and a plurality of tabs for forming a first fuse with the nozzle rail (455). The body has a plate like shape and includes a plurality of impingement holes (464), a first edge, a second edge, and a first airfoil cooling hole (470). The plurality of tabs includes a first tab (461) extending from the first edge, and a second tab (462) extending from the second edge. The second tab (462) is located in a different quadrant of the body than the first tab (461).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.