Cooled aerofoil for a gas turbine engine
US6264428A · kind A · utility
63Cited by
13References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 11, 2000 |
| Grant date | Jul 24, 2001 |
| Priority date | — |
| Expiry date | Jan 11, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A hollow cooled aerofoil blade (10) is provided with a central, lengthways extending plenum (16) and has pressure and suction flanks (20,15). The suction flank (15) has lengthways extending passages (21) therein that direct cooling air from the root region (13) into the central plenum (16). From the central plenum, the cooling air flows through a first set of apertures (27) into lengthways extending passages (28) in the pressure flank (20). The cooling air then flows through a second set of apertures (30) in the pressure flank to provide film cooling of the pressure flank (20) external surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.