Patent ID: 7625179
Filing Date: 2009-12-01
Classification: F01D,F05D

Abstract:
1. A turbine engine component comprising: an airfoil portion having a pressure side wall and a suction side wall, a plurality of ribs extending between said pressure side wall and said suction side wall, and a plurality of supply cavities located between said ribs; and an arrangement for cooling said airfoil portion comprising a first means embedded within said suction side wall for convectively cooling said suction side wall, a second means embedded within said pressure side wall for cooling said pressure side wall, and third means for increasing a temperature of at least one of said ribs by conducting fluid through said at least one of said ribs, wherein said first means comprises a first cooling circuit embedded within said suction side wall, said second means comprises a second cooling circuit embedded within said pressure side wall, and said third means comprises at least one fluid passageway in a first one of said ribs for conducting fluid from said first cooling circuit to said second cooling circuit.