GAS TURBINE ENGINE AIRFOIL LEADING EDGE COOLING

摘要

A gas turbine engine component includes an airfoil (72) having a leading edge area (100), a first circuit to cool a first section of the leading edge area (100), and a second circuit to cool a second section of the leading edge area (100). The first circuit is separate and distinct from the second circuit within the airfoil (72). A gas turbine engine (10) comprising variable vanes array (60) upstream of such airfoils (72). A corresponding method of cooling such an airfoil (72).