Patent ID: 6354795
Filing Date: 2002-03-12
Classification: F01D,F05D

Abstract:
A turbine cooling component for a turbine engine, which comprises:(a) a circumferential leading edge; (b) a circumferential trailing edge spaced from the leading edge; (c) an arcuate base connected to the trailing and leading edges and having a back surface and an arcuate inner surface that is in contact with the main hot gas stream of the turbine engine moving in the direction from the leading edge to the trailing edge of the turbine component; (d) a pair of spaced opposed side panels connected to the leading and trailing edges, each of the side panels having a leading section, a midsection and trailing section; (e) a plurality of cooling air passages extending through the base from the back surface thereof and having outlets exiting from at least one of the leading edge, the side panels and the inner surface of the base; (f) wherein all of the plurality of cooling air passages having outlets that exit from the leading or midsections of each side panel are skewed so that cooling air exits therefrom in a direction opposed to the main hot gas stream; (g) wherein at least one of the plurality of cooling air passages is an impingement cooling air passage, which has an outlet that exits from the midsection of one of the side panels and wherein at least another of the plurality of cooling air passages is an impingement cooling air passage, which has an outlet that exits from the midsection of the other side panel, and (h) a spline seal slot that extends from the leading section to the trailing section of each side panel, the slot having a humped section in at least the midsection of the side panel that is above and across at least the outlets of the cooling air passages exiting from the midsection of the side panel.