Tapered tip-rib turbine blade
US6190129A · kind A · utility
82Cited by
16References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 21, 1998 |
| Grant date | Feb 20, 2001 |
| Priority date | — |
| Expiry date | Dec 21, 2018 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/292
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine rotor blade 18 includes a dovetail 22 and integral airfoil 24. The airfoil includes a pair of sidewalls 28,30 extending between leading and trailing edges 32,34, and longitudinally between a root 36 and tip 38. The sidewalls are spaced laterally apart to define a flow channel 40 for channeling cooling air through the airfoil. The tip includes a floor 48 atop the flow channel, and a pair of ribs 50,52 laterally offset from respective sidewalls. The ribs are longitudinally tapered for increasing cooling conduction thereof.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.