Refraktärmetallkernkühltechnologie für gebogene Anströmkantennuten

摘要

A turbine engine component has an airfoil portion (12) with a leading edge portion (10). The leading edge portion (10) includes a plurality of staggered holes (14) for causing fluid to flow over a surface of the airfoil portion (10). A method for forming the leading edge portion (10) using refractory metal core technology is described.