Turbine blade with multiple impingement cooled passages
US8517684B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 14, 2008 |
| Grant date | Aug 27, 2013 |
| Priority date | — |
| Expiry date | Jan 20, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/22141
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine rotor blade with a serpentine flow cooling circuit having three legs in which the first leg and the second leg are upward flowing channels each having a series of slanted ribs that define impingement chambers with impingement cooling holes to provide impingement cooling to the airfoil walls. The second leg is a downward flowing leg that contains no metering holes and is substantially unobstructed to the cooling air flow. The rotation of the blade produces a centrifugal force on the airflow passing through the channels with the metering and impingement holes to aid in the flow towards the blade tip. The return channels are unobstructed in order to minimize the pressure loss on the return channel of the serpentine circuit.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.