Ceramic matrix composite vane structure for a gas turbine engine, corresponding low pressure turbine and assembling method

摘要

A vane structure (64A, 64B) for a gas turbine engine (20) includes a multiple of ceramic matrix composite (CMC) airfoil sections (70) integrated between a CMC outer ring (66) and a metal alloy inner ring (68). A corresponding low pressure turbine (46) and an assembling method are also provided.