Ceramic matrix composite airfoil segment for a gas turbine engine, corresponding structure and method of assembling

摘要

A ceramic matrix composite (CMC) airfoil segment (82) for a gas turbine engine (20) includes a box-shape fiber geometry (98A) which defines a rectilinear pressure side bond line (100P) and a rectilinear suction side bond line (100S). A corresponding structure and method of assembling are also provided.