High pressure turbine vane cooling hole distrubution
US8568085B2 · kind B2 · utility
5Cited by
58References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 19, 2010 |
| Grant date | Oct 29, 2013 |
| Priority date | — |
| Expiry date | Jun 30, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, third and fourth sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.