Bearing system with independent adaptive stifness support

A gas turbine engine, the gas turbine engine comprising:

• a fan assembly, wherein the fan assembly comprises a plurality of fan blades and a vane assembly;
• a core engine configured to drive the plurality of fan blades of the fan assembly;
• and
• a bearing system positioned at one or more of the core engine, the plurality of fan blades, and the vane assembly, wherein the bearing system is configured to surround a rotor of at least one of the core engine and the fan assembly along a circumferential direction corresponding to the rotor, wherein the rotor is extended along an axial direction co-directional to a centerline axis of the rotor, wherein the bearing system comprises:
• a body;
• a plurality of first support members;
• and
• a plurality of first housings, wherein is each of the plurality of first support members extends from the body to a respective one of the plurality of first housings, wherein the plurality of first support members are spaced apart from one another along the circumferential direction, wherein the plurality of first housings are spaced apart from one another along the circumferential direction;
• wherein each first support member comprises:
• a first axial support arm extended along the axial direction;
• and
• a first radial support arm extended from the first axial support arm along a radial direction;
• and
• wherein each of the plurality of first housings includes a bearing element in contact with a bearing surface at the rotor.