Cooling microcircuits for turbine airfoils

摘要

A cooling microcircuit (100) for use in a turbine engine component, such as a turbine blade, having an airfoil portion is provided. The cooling microcircuit (100) has at least one inlet slot (102) for introducing a flow of coolant into the cooling microcircuit (100), a plurality of fluid exit slots (106) for distributing a film of the coolant over the airfoil portion, and structures (108) for substantially preventing one jet of the coolant exiting through one of the fluid exit slots (106) from overpowering a second jet of the coolant exiting through the one fluid exit slot (106).