| 摘要 |
A turbine engine component (100), such as a turbine blade has an airfoil portion (102) with an airfoil mean line (138), a pressure side (130), and a suction side (132). A first region (134) on the pressure side (130) of the airfoil portion (102) has a first array of cooling microcircuits embedded in a wall forming the pressure side (130). A second region (136) on the pressure side (130) has a second array of cooling microcircuits embedded in the wall. The first region (134) is located on a first side of the mean line (138) and the second region (136) is located on a second side of the mean line (138). |
