LINER FOR A GAS TURBINE ENGINE

摘要

A gas turbine engine (100) is provided having a fan case (112) and a translating sleeve (127) positioned downstream from the fan case. A flow channel (102) extends between the fan case and the translating sleeve. The flow channel includes an inner diameter (108) and an outer diameter (110). A structural guide vane (116) is positioned within the flow channel and extends from the inner diameter to the outer diameter. A liner (200) is positioned between an aft end of the fan case and an aft end of the translating sleeve to reduce vibratory stress on the structural guide vane.