Hybrid spinner support

1. A fan section for a gas turbine aircraft engine, the fan section having a plurality of circumferentially spaced fan blades mounted to a fan rotor disk and fan platforms circumferentially located between the fan blades, a radially outer surface of the fan platforms defining part of a flow path for air between the fan blades at a radially inner end of the fan blades, the fan section further including a hybrid support ring, the hybrid support ring comprising:

a circumferentially-extending suspender having an inner surface and an outer surface, said suspender extending axially and having a forward end and a rearward end with a frusto conical leg extending between the forward end and the aft end and a forward flange extending radially inwardly from said forward end and having a plurality of apertures therein;

said suspender further including a lug which is thickened in an axial aft direction compared to forward portions of the leg and a circumferentially-extending groove in one of said inner surface and said outer surface adjacent to said rearward end; and

a belt extending circumferentially in and engaging said groove of said suspender;

said suspender being formed of a first metallic material and said belt being formed of a second non-metallic composite material;

wherein said belt accepts a loading from the fan platforms.

2. The fan section of claim 1 , said belt being formed of continuous wrapped composite.

3. The fan section of claim 2 further comprising chopped fiber composite.

4. The fan section of claim 1 , said suspender being formed of aluminum.

5. The fan section of claim 1 , said belt being interference fit in said groove.

6. The fan section of claim 1 , said flange having a lower lip.