INTEGRATED FAN CASE AND BEARING SUPPORT FOR A GAS TURBINE ENGINE AND METHOD

A unitary fan inlet case and bearing support structure (140) for a gas turbine engine includes an annular body (100) having a radially inward ring (120) connected to a radially outward ring (110) via a plurality of struts (130). A platform protrudes radially inward from the radially inward ring. The platform includes a radially outward facing surface and a radially inward facing surface. The annular body is a single unitary structure.