Abstract: A gas turbine engine including a compressor, a turbine and a static structure is disclosed herein. The gas turbine engine further includes a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure. The foil bearing system includes a foil bearing and a self-aligning foil bearing mount to align the foil bearing with an axis of rotation of the compressor and the turbine. A snubber operative to transmit rotor loads to the static structure in parallel with the foil bearing is also disclosed.

Abstract: One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique turbine engine. Another embodiment is a unique turbine engine powered system. Another embodiment is a hybrid bearing system for use in a turbine engine and/or a turbine engine powered system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for hybrid bearings, turbine engine systems with one or more hybrid bearings and turbine engine powered systems with one or more hybrid bearings. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A gas turbine engine bearing assembly for a portion of a shaft that rotates around an axis, including a substantially cylindrical bearing having a length extending between a first end and a second end along the axis of the rotating shaft. A plurality of segmented damper springs are positioned around an exterior perimeter of a portion of the cylindrical bearing. Each spring has a width along the axis of the rotating shaft and a portion of each spring defines an outer spherically contoured joint. The width of each spring is less than the length of the bearing.

Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine foil bearing system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine bearing systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique augmented gas turbine engine propulsion system. Another embodiment is a gas turbine engine power augmentation system. Yet another embodiment is a system for augmenting power in an engine powered air vehicle. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique turbine engine. Another embodiment is a unique turbine engine powered system. Another embodiment is a hybrid bearing system for use in a turbine engine and/or a turbine engine powered system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for hybrid bearings, turbine engine systems with one or more hybrid bearings and turbine engine powered systems with one or more hybrid bearings. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A gas turbine engine bearing assembly for a portion of a shaft that rotates around an axis, including a substantially cylindrical bearing having a length extending between a first end and a second end along the axis of the rotating shaft. A plurality of segmented damper springs are positioned around an exterior perimeter of a portion of the cylindrical bearing. Each spring has a width along the axis of the rotating shaft and a portion of each spring defines an outer spherically contoured joint. The width of each spring is less than the length of the bearing.

Abstract: A fluid damping system for damping a shaft within a gas turbine engine component. The fluid damping system including a damping liquid and a pressurized gas in a closed self contained system. In one aspect the damping liquid is cooled by being disposed in a heat transfer relationship with a fuel.