Patent ID: 6402464
Filing Date: 2002-06-11
Classification: F01D,F05D,Y10S

Abstract:
A turbine component comprising an element separating a high-temperature region and a cooling medium from one another, said element on a cooling medium side thereof having a surface with discrete bumps separated from one another and projecting from said surface, said surface with said discrete bumps defining a predetermined ratio of the area of said surface with said bumps and the area of said surface without said bumps, a surface coating on said cooling medium side of said element overlying said surface with discrete bumps forming a cooling side surface having a ratio of the area of said coated surface with said bumps and the area of said surface with said bumps without said coating in excess of said predetermined surface area ratio to afford increased heat transfer between the cooling medium and the element relative to the heat transfer between the cooling medium and the element without said coating.