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 unique gas turbine engine. Another embodiment is a unique machine. A further embodiment is a unique self-aligning foil bearing system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for machines and self-aligning foil bearing systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

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 unique gas turbine engine. Another embodiment is a unique machine. A further embodiment is a unique self-aligning foil bearing system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for machines and self-aligning foil bearing systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

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.

Abstract: A turbomachine including a case, a rotor, a plurality of rotor blades on the rotor each having a blade tip, a shroud around the rotor blade tips, and bearings mounting the rotor on the case for rotation about a centerline of the case and for bodily shiftable movement in the direction of the centerline. The rotor blade tips and an inside wall of the shroud flare radially outward in the direction of the centerline so that when the rotor moves in the direction of the centerline toward the shroud a clearance gap between the blade tips and the inner wall of the shroud decreases and vice versa. An electromagnetic actuator on the case magnetically attracts a thrust plate on the rotor against a net dynamic force on the rotor. A control system of the actuator controls the magnetic attraction of the actuator in response to signals from a position sensor measuring the actual magnitude of the clearance gap to maintain the actual clearance gap at a predetermined magnitude.

Abstract: A vibration damper of a rotating shaft includes a floating housing attached to the shaft for radial vibratory displacement as a unit therewith, a plurality of cylindrical bores in the floating housing parallel to the axis of rotation of the shaft, and a plurality of smaller cylindrical impactors in the cylindrical bores. Each impactor is a metal sleeve having a smaller cylindrical tungsten rod therein with a damping medium around the rod. When the shaft experiences radial vibratory displacement, the sleeves impact the bores. When the sleeves impact the bores, the damping medium is squeezed from between the tungsten rods and the sleeves for vibration damping energy absorption in one mode. In addition, the tungsten rods impact the bores through the sleeves and initiate local plastic deformation of the bores the sleeves and the rods for energy absorption in another mode.

Abstract: An engine turbocharger, particularly of the two cycle diesel type for railway locomotives and other applications, has a rotor with an overhung compressor supported by a compressor journal bearing and thrust flange combination. The bearing combines a multi (two) lobed offset cylindrical wedge film inner surface with a close clearance squeeze film outer surface that causes the bearing to float laterally in a support member to damp shaft runout while supporting the rotor on load controlling oil wedges. The fixed flange provides thrust control and provides a loose pin connection with the bearing that prevents rotation while permitting its squeeze film damping lateral motion. Particular pressure lubrication provides oil to the bearing interior and exterior adequate for the oil wedge supporting and squeeze film damping functions.

Abstract: A squeeze film damper for the high temperature environments includes a fixed journal on a support, a floating journal on a rotating shaft, a damping ring in an annular chamber between the fixed and floating journals, and a pair of metal bellows straddling annular exposed channels defined at a pair of clearance gaps between the fixed and floating journals. The metal bellows are welded to the fixed and floating journals on opposite sides of the exposed channels and filled with high temperature resistant viscous fluid. The damping fluid flows to the damping chamber through the annular channels and the clearance gap between the fixed and floating journals.

Abstract: A squeeze film damper for dynamically unbalanced rotor includes a bearing on the rotor having a non-rotatable outer race which is vibrateable as a unit with the rotor, on outer plain cylindrical surface on the bearing outer race, an inner plain cylindrical surface on a support around the outer surface concentric therewith when the rotor is aligned on a nominal axis of the support and cooperable therewith in defining a small annulus having a radial depth corresponding to the maximum radial vibratory displacement of the rotor, a groove in the inner cylindrical surface of axial length of between about 1/2 and 2/3 of the axial length of the small annulus and cooperable with the outer plain surface in defining a large annulus having a radial depth of at least three times the small annulus radial depth, the groove being axially symmetrical with respect to the small annulus, and means for maintaining the small and large annuli filled with fluid under pressure.

Abstract: In a mount for a bearing on a high speed shaft subject to radial and axial vibratory displacement, a tube around the shaft having a first end rigidly connected to the bearing so that the tube vibrates with the shaft, an annular diaphragm spring with an inner diameter whereat a second end of the tube is rigidly attached and an outer diameter and a resilient planar portion therebetween, an annular shim between the diaphragm spring and a stationary parallel surface, a seal between the diaphragm spring and the parallel surface which cooperates with the shim and the parallel surface and the diaphragm spring planar portion in defining an annular squeeze film chamber, and means for maintaining the squeeze film chamber filled with fluid. When the shaft vibrates radially, the diaphragm spring planar portion distorts and the distortion orbits the squeeze film chamber wherein a resisting force is developed by the fluid to damp the vibrations.

Abstract: A squeeze film damping type bearing mount between a bore in a support structure and an outer race of a shaft bearing, the bearing mount including a first adapter rigidly attached to the support structure with a cylindrical flange thereof projecting into the annulus between the bore and the outer race, a second adapter rigidly attached to the outer race with a cylindrical flange thereof projecting into the annulus radially outboard of the other flange, and a wave spring in the annular chamber between the two flanges to maintain concentricity between the outer race and the bore. The first adapter cylindrical flange cooperates with the outer race in defining an inner squeeze film annulus, the second adapter flange cooperates with the bore in defining an outer squeeze film annulus, and means are provided to maintain both annuli filled with hydraulic fluid to effect squeeze film damping.

Abstract: A passive aircraft landing gear system in which the spring rate and damping for aircraft rolling motions about a longitudinal axis are independent of the spring rate and damping for aircraft vertical motions, thereby permitting the landing gear system to optimally accomplish both landing impact attenuation and ground resonance instability abatement.