System and method for gas bearing support of turbine

A bearing assembly for a turbine engine comprising:

• a first gas bearing configured to receive a first load from a rotating low pressure turbine (LPT) shaft of the turbine engine;
• a gas delivery disk configured to receive the first load and a second load from a rotating high pressure turbine (HPT) shaft of the turbine engine disposed concentrically about the LPT shaft, wherein the gas delivery disk comprises:
• an inner axial opening configured to facilitate a first axial flow through a first passage disposed between the HPT shaft and the LPT shaft;
• a middle axial opening configured to facilitate a second axial flow through a second passage disposed radially exterior to the HPT shaft;
• and
• a duct configured to extract a bearing flow from the second axial flow and to supply the bearing flow in a radial direction to the first gas bearing;
• and
• a damping member coupled to a casing of a combustor section of the turbine engine, wherein the damping member is configured to receive the first load and the second load from the gas delivery disk.

A method comprising:

• transferring a load from a first gas bearing disposed about a shaft of a turbine engine to a transmission disk, wherein the load comprises a static load on the shaft, a dynamic load on the shaft, or any combination thereof;
• transferring the load from the transmission disk to a casing of a combustor section of the turbine engine;
• and
• damping the load transferred to the casing via a damping member, wherein the damping member comprises a second gas bearing.