Abstract: A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.

Abstract: A support system for a gas turbine engine is provided. The support system includes a load-bearing unit that includes a first flange, a support element supporting the load-bearing unit and having a second flange, a fastener connecting the first flange and the second flange, a first super-elastic shape memory alloy component in contact with the first flange, and a second super-elastic shape memory alloy component in contact with the second flange. The first and the second super-elastic shape memory alloy components are configured to deform when a load exerted by the fastener exceeds a threshold load value of the fastener.

Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal ci

Abstract: A rotor support system for a gas turbine engine is disclosed. The rotor support system includes a bearing support flange, a frame support flange proximate to the bearing support flange, a fastener between the bearing support flange and the frame support flange, a damping component, and an axial retainer. The damping component includes a super-elastic shape memory alloy. The fastener is configured to fail when a load on the fastener exceeds a threshold value and the damping component is configured to deform from a normal state to a deformed state after the fastener fails. The axial retainer is configured to retain the bearing support flange and the frame support flange within an axial displacement from each other after the fastener fails. A radial gap exists between the bearing support flange and the frame support flange when the damping component is in the normal state.