Patent ID: 8220522
Filing Date: 2012-07-17
Classification: B22C,F01D,F05D,F28F,Y02T,Y10T

Abstract:
1. A process for forming an airfoil portion of a turbine engine component comprising the steps of: placing at least one silica core for forming a central core element in a die; providing at least one refractory metal core element having a serpentine configuration, said serpentine configuration having a first leg for forming an inlet leg of said cooling passageway, said first leg having at least one first tab for forming at least one inlet extending in a first direction, said at least one first tab being located inwardly of an outer edge of said first leg, a second leg for forming an outlet leg of said cooling passageway, said second leg having at least one second tab extending in a second direction opposed to said first direction for forming at least one cooling hole; placing said at least one refractory metal core element for forming at least one serpentine cooling passageway in said die; and forming the airfoil portion by introducing a metal material into said die so that said metal material flows around said at least one silica core and said at least one refractory metal core element so as to form an airfoil portion having a pair of walls and at least one serpentine cooling passageway in one of said walls.