Heat transferring cooling features for an airfoil
US7217095B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 9, 2004 |
| Grant date | May 15, 2007 |
| Priority date | — |
| Expiry date | Mar 29, 2025 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade airfoil assembly includes a cooling air passage. The cooling air passage includes a plurality of impingement openings that are isolated from at least one adjacent impingement opening. The cooling air passage is formed and cast within a turbine blade assembly through the use of a single core. The single core forms the features required to fabricate the various separate and isolated impingement openings. The isolation and combination of impingement openings provides for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.