Abstract: A coating to reduce friction, the coating including an amorphous metal, and a solid lubricant. The solid lubricant may be dispersed with the amorphous metal throughout the coating, or the solid lubricant may form a layer on top of the amorphous metal. The coating may be applied to various components such as aircraft components, gas turbine engine components, etc., to reduce friction.

Abstract: A bearing assembly includes a bearing, an outer race located radially outward of the bearing and supporting the bearing, a bearing housing located radially outward of the outer race and supporting the bearing and the outer race, and a bearing lubricant drain including a multi-directional passage formed in one or both of the outer race or the bearing housing, the lubricant drain arranged to cause a lubricant to flow from a first location to a second location. The second location is radially outward and axially offset from the first location. A gas turbine engine includes a shaft configured to rotate about a centerline axis of the gas turbine engine and the bearing assembly configured to facilitate the rotation of the shaft.

Abstract: A coated component is provided that has a relatively low friction coating across a broad temperature range. The coated component includes a substrate having a surface and a wear coating over the surface of the substrate. The wear coating includes dual lubricant constituents diffused within a matrix phase. The wear coating may have an operating temperature range of 35° C. to 850° C. while having a coefficient of friction that is 0.15 to 0.5.

Abstract: Oleophobic and/or oleophilic coatings to reduce heat loads on a gas turbine engine thermal management system are disclosed herein. An example method to reduce heat load in a gas turbine engine, the method including applying an oleophobic coating to an internal wall of a sump, the sump located in proximity to a heat generating element of the gas turbine engine, and applying an oleophilic coating to the heat generating element of the gas turbine engine.

Abstract: Bearing assemblies for a turbomachine include a first race statically coupled to a fixed engine housing, a second race coupled to a rotating shaft, a bearing cage disposed between the first race and the second race, and at least one bearing element disposed in the bearing cage. The bearing cage can include inlet channels to allow air to flow into the bearing cage and outlet channels that allow the air and lubricant mixture in the bearing cage to vent into adjacent compartments of the turbomachine. During operation, the inlet channels actively direct an airflow into the bearing cage. In the bearing cage, the air mixes with lubricant, and the air and lubricant mixture is expelled from the bearing cage through the outlet channels, thereby reducing dwell time of lubricant in the bearing assembly.

Abstract: Oleophobic and/or oleophilic coatings to reduce heat loads on a gas turbine engine thermal management system are disclosed herein. An example method to reduce heat load in a gas turbine engine, the method including applying an oleophobic coating to an internal wall of a sump, the sump located in proximity to a heat generating element of the gas turbine engine, and applying an oleophilic coating to the heat generating element of the gas turbine engine.

Abstract: Oleophobic and/or oleophilic coatings to reduce heat loads on a gas turbine engine thermal management system are disclosed herein. An example method to reduce heat load in a gas turbine engine includes applying an oleophobic coating to an internal wall of a sump, the sump located in proximity to a heat generating element of the gas turbine engine, and applying an oleophilic coating to the heat generating element of the gas turbine engine, the heat generating element positioned in a cavity of the sump.

Abstract: A bearing assembly includes a bearing, an outer race located radially outward of the bearing and supporting the bearing, a bearing housing located radially outward of the outer race and supporting the bearing and the outer race, and a bearing lubricant drain including a multi-directional passage formed in one or both of the outer race or the bearing housing, the lubricant drain arranged to cause a lubricant to flow from a first location to a second location. The second location is radially outward and axially offset from the first location. A gas turbine engine includes a shaft configured to rotate about a centerline axis of the gas turbine engine and the bearing assembly configured to facilitate the rotation of the shaft.

Abstract: A method for predicting a remaining useful life of a bearing involves obtaining a plurality of sets of actual inspection data from the bearing. The method involves obtaining an estimated wear rate from a physics based model of the bearing. The method further involves adjusting the estimated wear rate based on the plurality of sets of actual inspection data to compute an actual wear rate. The method also involves computing a calibration parameter based on the actual wear rate. The method further involves predicting a remaining useful life of the bearing based on the calibration parameter.

Abstract: A method (60, 90) includes executing a wear protocol to derive a start-stop (SS) wear, a steady-state operating hours (OH) wear, or a combination thereof, of a test journal bearing system (10). The method (60, 90) further includes observing operations of an engine (8) via one or more sensors to determine a number of start-stops, steady-state operating hours, or a combination thereof. The method (60, 90) also includes determining a determined journal bearing system wear (114) based on applying a physics-based model (94) of a journal bearing system (10) and the transfer function to the number of start-stops, the steady-state operating hours, or to the combination thereof. The method (60, 90) additionally includes executing one or more actionable items (116) on the engine (8) based on the determined journal bearing system wear (114).

Abstract: A method for predicting a remaining useful life of a bearing involves obtaining a plurality of sets of actual inspection data from the bearing. The method involves obtaining an estimated wear rate from a physics based model of the bearing. The method further involves adjusting the estimated wear rate based on the plurality of sets of actual inspection data to compute an actual wear rate. The method also involves computing a calibration parameter based on the actual wear rate. The method further involves predicting a remaining useful life of the bearing based on the calibration parameter.

Abstract: A method for estimating life of a piston ring includes obtaining a reference profile of the piston ring. The reference profile comprises a plurality of reference fiducials. The method further includes receiving a measured profile of the piston ring. The measured profile comprises a plurality of measured fiducials. The method further includes aligning the measured profile with the reference profile based on one or more of the plurality of reference fiducials and one or more of the plurality of measured fiducials. The method also includes determining one or more wear parameters based on the aligned measured profile and the reference profile. The method also includes generating a wear model based on the one or more wear parameters. The method also includes estimating a life of the piston ring based on the wear model.

Abstract: A method (60, 90) includes executing a wear protocol to derive a start-stop (SS) wear, a steady-state operating hours (OH) wear, or a combination thereof, of a test journal bearing system (10). The method (60, 90) further includes observing operations of an engine (8) via one or more sensors to determine a number of start-stops, steady-state operating hours, or a combination thereof. The method (60, 90) also includes determining a determined journal bearing system wear (114) based on applying a physics-based model (94) of a journal bearing system (10) and the transfer function to the number of start-stops, the steady-state operating hours, or to the combination thereof. The method (60, 90) additionally includes executing one or more actionable items (116) on the engine (8) based on the determined journal bearing system wear (114).