Abstract: A fan frame (10) for a gas turbine is provided. The fan frame (10) has fan exit guide vanes (100) that are connected to an intermediate case (50) for structural support, and are constrained from movement in a radial direction by a first joint (110, 110a) and constrained from movement in an axial and radial direction by a second joint (120a, 110a). The intermediate case (50) provides structural integrity while reducing weight by providing struts (56, 95) with a width that increases in a direction away from a central bearing (55) as the thickness of the struts (56, 95) decreases.

Abstract: A fan frame (10) for a gas turbine is provided. The fan frame (10) has fan exit guide vanes (100) that are connected to an intermediate case (50) for structural support, and are constrained from movement in a radial direction by a first joint (110, 110a) and constrained from movement in an axial and radial direction by a second joint (120a, 110a). The intermediate case (50) provides structural integrity while reducing weight by providing struts (56, 95) with a width that increases in a direction away from a central bearing (55) as the thickness of the struts (56, 95) decreases.

Abstract: A bearing support for a rotor of an aircraft turbine engine which includes a front bearing and a front bearing support and bearing strut for securely attaching the front bearing, to the aircraft turbine engine support structure, wherein the front bearing support and bearing strut are integral with the aircraft turbine engine support structure.