Patent ID: 7607890

Claim:
A cooling microcircuit for use in a turbine engine component having an airfoil portion, said microcircuit comprising: at least one inlet slot for introducing a flow of coolant into said cooling microcircuit; a plurality of fluid exit slots for distributing a film of said coolant over said airfoil portion; each of said exit slots being provided with means for substantially preventing one jet of said coolant exiting through said fluid exit slot from overpowering a second jet of said coolant exiting through said fluid exit slot; each said exit slot being formed by a pair of first sidewall portions and a pair of second sidewall portions joined to said first sidewall portions; said means for substantially preventing one jet from overpowering a second jet comprising a pedestal aligned with said first sidewall portions so as to form a pair of channel each having a length sufficient to allow a flow of cooling fluid to settle down and straighten out; each said pedestal having an arcuately shaped leading edge portion, arcuately shaped portions joined to ends of said leading edge portion, and a trailing edge portion formed by two side portions joined to said arcuately shaped portions and a tip portion joining said two side portions; and each of said first sidewall portions beginning from a point substantially aligned with said leading edge portion of each said pedestal and extending to a point substantially aligned with said tip portion of each said pedestal.