Patent ID: 7739866

Claim:
A casing for an aircraft turbofan bypass engine, the casing comprising: a thin-walled sheet metal annular case adapted to encircle the engine and having a plurality of engine mounts thereon adapted to mount the engine to an aircraft, airflow through the engine in use defining upstream and downstream directions; a plurality of thin-walled sheet metal struts connected to an annular leading edge tip of a splitter separating a core flow passage from a bypass flow passage, the struts having a leading edge extending uninterruptedly between an engine bearing support structure and the case, the strut leading edges connected to the engine bearing support structure axially upstream of where the strut leading edges connect to the case thus angling the strut leading edges rearwardly as they extends radially outwardly, the engine bearing support structure disposed inwardly of the core flow passage, the strut leading edges disposed upstream of the splitter leading edge tip such that the strut leading edges provide an uninterrupted primary load path from the engine bearing support structure to the case for transfer of thrust loading from engine bearing support structure to the engine mounts on the case, the struts each having a centroidal axis defined along a locus of centroid positions for a plurality of strut sections along a length of the strut, wherein the engine mounts are axially and circumferentially positioned on the case to substantially correspond with one of said strut centroidal axes to thereby minimize bending loads in the case as a result of thrust loads transferred by the struts to the engine mounts.