TURBINE ENGINE AIRFOIL INSERT

An apparatus and method for improving the heat transfer coefficient for an engine component for a turbine engine such as an airfoil. The airfoil can include an outer wall defining an interior. A cooling passage can be formed in the interior defining a flow direction. An insert can be provided in the cooling passage to occupy a volume of the cooling passage to maintain a threshold Mach number for an airflow passing through the cooling passage to improve the heat transfer coefficient. 本申请涉及涡轮发动机翼型件的插入件。其中，种用于改善用于涡轮发动机的发动机构件如翼型件的传热系数的设备及方法。翼型件可包括限定内部的外壁。冷却通路可形成在限定流动方向的内部中。插入件可设在冷却通路中来占据冷却通路的容积，以保持穿过冷却通路的空气流的阈值马赫数来改善传热系数。