STRESS MITIGATION FEATURE FOR COMPOSITE AIRFOIL LEADING EDGE

摘要

A vane assembly within a mid-turbine frame of a gas turbine engine includes an airfoil that extends between an outer platform and an inner platform. The airfoil includes an outer wall defining a leading edge of a first radius. An inner wall of the airfoil defines an inner cavity including a forward portion proximate the leading edge defining a second radius different than the first radius.

主权项

1. An airfoil assembly comprising:
an outer wall defining a leading edge of a first radius; and an inner wall defining a second radius adjacent the leading edge that is larger than the first radius.