Patent ID: 8757958

Claim:
A gas turbine engine fan section comprising: a body including main and outer composite layers providing a generally cylindrical case; axially spaced apart rings arranged between the main and outer composite layers forming forward and aft reinforcing ribs and providing a fan containment area axially there between; an inner composite layer providing a fan blade rub resistant surface, wherein the main composite layer is adhered to the inner composite layer, the rings adjoining the main composite layer; a honeycomb structure provided axially between the reinforcing ribs; a belt arranged over and spanning the fan containment area between the forward and aft reinforcing ribs, the belt extending axially forward of the forward reinforcing rib to secure the belt to the body, and the belt extending axially rearward of the aft reinforcing rib to secure the belt to the body; and a fan blade having a tip in proximity to the inner composite layer without any intervening structural support between the tip and the inner composite layer.