Turbine nozzle with trailing edge convection and film cooling
US7503749B2 · kind B2 · utility
6Cited by
4References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 1, 2005 |
| Grant date | Mar 17, 2009 |
| Priority date | — |
| Expiry date | Nov 23, 2026 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine has opposed pressure and suction sidewalls extending between a leading edge and a trailing edge. The airfoil includes an array of radially-spaced apart longitudinally-extending lands which define a plurality of trailing edge slots therebetween. Each of the trailing edge slots has an inlet in fluid communication with an interior of the airfoil and an exit in fluid communication with the trailing edge. At least one of the lands is tapered such that a width of the land measured in a radial direction decreases from the suction sidewall to the pressure sidewall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.