Gas turbine engine with ceramic matrix composite static structure and rotor module, and corresponding method of tip clearance control

摘要

A gas turbine engine (20) includes a ceramic matrix composite (CMC) static structure (60) and a rotor module (62) with a multiple of CMC airfoils (66), a radial growth of said rotor module (62) matched with said CMC static structure (60). A corresponding method of tip clearance control is also provided.