Abstract: A turbofan gas turbine engine is provided with a polygonal rigid frame formed by a hub member, a plurality of radially extending spokes and a plurality of straight members connect to the radially outer ends of the spokes. The hub member is secured to the core casing and the straight members are secured to the core casing and the straight members are secured to the fan casing. Brackets are provided at two hard points at the radially outer ends of two adjacent hard points at the radially outer end of two adjacent spokes and brackets are provided at two hard points at the radially inner ends of two other spokes. The spokes have a chord length of six times that of conventional outlet guide vanes. The hard points are connected by links to a bracket at a first axial position on the aircraft stub pylon extension and the hard points are connect by links to a bracket at a second axial position on the stub pylon extension to form a rigid triangular structure to mount the engine from the aircraft.

Abstract: A fan for a ducted fan gas turbine engine comprises a hub carrying an array of generally radially extending fan blades. The hub is hollow and tapered in an axial direction. The radially outer hub surface is provided with a plurality of generally axially extending slots. The slots receive corresponding stepped teeth provided on the radially inner ends of the fan blades. A nose cone engages the upstream end of the roots of the fan blades to ensure that the teeth are retained in the slots.