Abstract: A shaft assembly for a rotary machine, the rotary machine includes a low pressure compressor, a high pressure compressor, a high pressure turbine, and a low pressure turbine. The shaft assembly includes an outer shaft configured to couple the high pressure compressor to the high pressure turbine. The outer shaft includes a first forward bearing assembly positioned forward of the high pressure compressor, and a first aft bearing assembly positioned between the high pressure compressor and the high pressure turbine. The shaft assembly also includes an inner shaft rotatable about a common axis with the outer shaft that at least partially extends about the inner shaft. The inner shaft is configured to couple the low pressure compressor to the low pressure turbine. The inner shaft includes a second forward bearing assembly positioned forward of the low pressure compressor, and a second aft bearing assembly positioned proximate the high pressure turbine.

Abstract: A bearing includes a bearing pad for supporting a rotary component and a housing attached to or formed integrally with the bearing pad. The housing includes a flexible column extending towards the bearing pad for providing the bearing pad with an airflow. The column supports the bearing pad from a location inward of an outer periphery of the bearing pad along an axial direction of the bearing. With such a configuration, a resistance of the bearing pad along a radial direction of the bearing is less at the outer periphery than a resistance of the bearing pad along the radial direction proximate the column.

Abstract: A roller bearing cage includes a cylindrical body including a plurality of pocket holes defined within and positioned circumferentially about the cylindrical body. At least a portion of the cylindrical body is hollow. The roller bearing cage further includes a reinforcement structure extending within the portion of the cylindrical body. The reinforcement structure is configured to provide a stiffening force to the cylindrical body.

Abstract: One embodiment describes a bearing damper including a housing; a damper with an annular gap and an internal spring, in which the annular gap is formed between an inner rim and an outer rim of the damper, the internal spring circumferentially bounds the annular gap, the outer rim is coupled to the housing, and the annular gap is configured to be filled with fluid used to dampen vibrations produced on a drive shaft; and an external spring coupled to the housing and to the inner rim, in which the external includes an axial stiffness engineered to externally offset axial forces exerted on the inner rim of the and a radial stiffness engineered to externally offset a first portion of radial forces exerted on the inner rim and to permit a second portion of the radial forces to propagate the vibrations from the drive shaft to the inner rim.

Abstract: A system includes a gas delivery disk coupled to a second shaft, wherein the second shaft and the gas delivery disk are disposed about an axis. The gas delivery disk includes an inner axial opening configured to facilitate a first axial flow through a first passage within the second shaft, a duct configured to supply a bearing flow in a radial direction toward the axis, and a bearing face disposed within the first passage and radially interior to the inner axial opening. The bearing face is configured to receive the bearing flow, and the bearing face is configured to form a gas bearing between the bearing face and a first shaft disposed about the axis.

Abstract: A bearing assembly for a turbine engine includes a first gas bearing configured to receive a load from a rotating shaft of the turbine engine, a transmission disk configured to receive the load from the first gas bearing, and a damping member coupled to a casing of a combustor section of the turbine engine. The transmission disk includes a gas delivery disk, which includes an axial opening configured to facilitate an axial flow through the gas delivery disk and a duct configured to facilitate a radial flow through the gas delivery disk to form the first gas bearing. The damping member is configured to receive the load from the transmission disk.

Abstract: In one aspect, a dual pitch bearing configuration for coupling a rotor blade to a hub of a wind turbine. The dual pitch bearing configuration including a first pitch bearing and at least one additional pitch bearing disposed axially a distance LB from the first pitch bearing. The dual pitch bearing configuration further including one or more spacers disposed between the first pitch bearing and the at least one additional pitch bearing and extending the distance LB. The dual pitch bearing disposed radially within one of a blade root of the rotor blade, a hub extension or a bearing housing and coupled thereto. The dual pitch bearing configuration minimizing moment loading on the first pitch bearing and the at least one additional pitch bearing. A wind turbine including the dual pitch bearing configuration is further disclosed.

Abstract: One embodiment describes a bearing damper including a housing; a damper with an annular gap and an internal spring, in which the annular gap is formed between an inner rim and an outer rim of the damper, the internal spring circumferentially bounds the annular gap, the outer rim is coupled to the housing, and the annular gap is configured to be filled with fluid used to dampen vibrations produced on a drive shaft; and an external spring coupled to the housing and to the inner rim, in which the external includes an axial stiffness engineered to externally offset axial forces exerted on the inner rim of the and a radial stiffness engineered to externally offset a first portion of radial forces exerted on the inner rim and to permit a second portion of the radial forces to propagate the vibrations from the drive shaft to the inner rim.

Abstract: A bearing including a bearing pad and a housing is provided. The bearing pad has a thrust face for supporting a vibration along an axial direction of the bearing. Additionally, the housing is formed integrally using an additive manufacturing process and is attached to or formed integrally with the bearing pad. The housing defines a working gas delivery system for providing a flow of pressurized working gas to the thrust face of the bearing pad and a fluid damper cavity. The fluid damper cavity provides a dampening of the axial vibration supported by the thrust face of the bearing pad along the axial direction.

Abstract: The present disclosure is directed to a bearing assembly for a gas turbine engine. The bearing assembly includes a bearing housing and a bearing pad for supporting a rotary component of the gas turbine engine. The bearing pad includes at least one gas inlet and a plurality of gas outlets configured on an inner surface thereof. The gas inlet is in fluid communication with the plurality of gas outlets via a gas distribution labyrinth. Further, the gas distribution labyrinth includes a plurality of passageways configured to evenly distribute pressurized gas entering the gas inlet to an interface between the inner surface of the bearing pad and an outer diameter of the rotary component.

Abstract: Embodiments of a stage for a turbomachine have been provided herein. In some embodiments, a stage for a turbomachine may include a bearing having a housing, the bearing defining an interior cavity; an outer ring disposed radially outward from the housing; and a plurality of airfoils disposed between the housing of the bearing and the outer ring.

Abstract: The present disclosure is directed to a gas-lubricated bearing assembly for a gas turbine engine and method of damping same. The bearing assembly includes a bearing pad for supporting a rotary component and a bearing housing attached to or formed integrally with the bearing pad. The bearing housing includes a first fluid damper cavity, a second fluid damper cavity in restrictive flow communication with the first fluid damper cavity via a restrictive channel configured as a clearance gap, and a damper fluid configured within the first and second fluid damper cavities. More specifically, the damper fluid of the present disclosure is configured to withstand the high temperature environment of the engine. Thus, the bearing housing is configured to transfer the damper fluid from the first fluid damper cavity to the second fluid damper cavity via the restrictive channel in response to a force acting on the bearing pad.

Abstract: A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing.

Abstract: A rotary machine for an aeronautical device includes a thrust generator. The rotary machine additionally includes a rotary component rotatable with the thrust generator. Moreover, the rotary machine of the present disclosure includes a plurality of gas bearings, with the plurality of gas bearings substantially completely supporting the rotary component of the rotary machine.

Abstract: The present disclosure is directed to an oil-free gas turbine engine. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust nozzle section. Further, the gas turbine engine includes at least one rotary component configured to drivingly connect at least a portion of the turbine section to at least a portion of the compressor section. Moreover, the gas turbine engine includes one or more gas-lubricated bearings configured to support the rotary component. In addition, the gas turbine engine includes a direct-drive starter-generator configured to start the gas turbine engine. Thus, the gas turbine engine of the present disclosure provides an engine that is at least partially oil free.

Abstract: A bearing includes a bearing pad for supporting a rotary component and a housing attached to or formed integrally with the bearing pad. The housing includes a flexible column extending towards the bearing pad for providing the bearing pad with an airflow. The column supports the bearing pad from a location inward of an outer periphery of the bearing pad along an axial direction of the bearing. With such a configuration, a resistance of the bearing pad along a radial direction of the bearing is less at the outer periphery than a resistance of the bearing pad along the radial direction proximate the column.

Abstract: A bearing includes a bearing pad for supporting a rotary component and a housing attached to or formed integrally with the bearing pad. The housing defines a first fluid damper cavity positioned adjacent to the bearing pad and a second fluid damper cavity spaced from the first fluid damper cavity. The first and the second fluid damper cavities are in restrictive flow communication. The housing is configured to transfer a fluid from the first fluid damper cavity to the second fluid damper cavity in response to a force acting on the bearing pad to dampen a movement of the bearing pad.

Abstract: An assembly for flexibly damping a power gear box for a gas turbine engine, the assembly includes a flexible mount connected to the power gear box at a first end of the flexible mount; a member connected to the flexible mount at the first end of the flexible mount and a second end of the flexible mount, wherein the first end of the flexible mount includes an outer rim connected to the member and an inner rim connected to the power gear box and a set of circumferentially segmented squeeze film damper lands configured to receive a damping fluid is provided between the inner rim and the outer rim.

Abstract: An epicyclic gearing arrangement includes a planet gear rotatable on a planet bearing that is mounted via a support pin to a carrier of the epicyclic gearing arrangement. A spring film damper is disposed between the outer surface of the bearing's outer ring and the opposing inner surface of the planet gear and includes an annular gap. The support pin and/or outer ring include oil feed holes that open into the respective annular gap(s).

Abstract: An epicyclic gearing arrangement includes a planet gear rotatable on a planet bearing that is mounted via a support pin to a carrier of the epicyclic gearing arrangement. A spring film damper is disposed between the cylindrical outer surface of the support pin and the opposing inner surface of the inner ring of the planet bearing and includes an annular gap.