General Electric Company
FAN CASE FOR A GAS TURBINE ENGINE

Abstract:

A fan case for a gas turbine engine including a first end, a second end, and an annular casing wall extending between the first end and the second end, the annular casing wall having a radially inner surface, a radially outer surface, and a thickness defined between the radially inner surface and the radially outer surface, and the annular casing wall also having diametrically-opposed first and second circumferential locations, wherein the thickness of the annular casing wall varies from a minimum thickness at the first circumferential location to a maximum thickness at the second circumferential location.