Abstract: A bearing assembly includes a shaft and a thrust runner attached to the shaft. The shaft runner protrudes radially outward from the shaft. A thrust bearing is positioned axially adjacent to the thrust runner. A first flow passage is between the thrust runner and a first face of the thrust bearing. A second flow passage is between a second face of the thrust bearing and a housing. A restriction feature restricts a flow of fluid through the second flow passage.

Abstract: A gas bearing within a cylinder is provided. The gas bearing comprises an anti-rotation tab sitting within a key way of the cylinder. Further, the gas bearing comprises a first foil forming an inner loop and an intermediary loop. The inner loop extends in a first direction from a first end to an intermediary portion. The intermediary loop extends from the intermediary to the anti-rotation tab.

Abstract: An air separation module includes a plurality of fibers located within a casing. A fiber membrane defines an exterior of each of the plurality of fibers. The fiber membrane also forms an interior passage along a length of each of the plurality of fibers. The fiber membrane is configured to permeate a gas through the fiber membrane. At least one perforated canister is placed between the plurality of fibers. The at least one perforated canister is configured to collect a permeated gas from the plurality of fibers.

Abstract: A sensor supply tube assembly is provided for disposition within a compressor outlet through which a main flowpath is defined and a sensor port transversely coupled to the compressor outlet. The sensor supply tube assembly includes first and second tubes. The first tube is formed to direct main flowpath fluid from the compressor outlet and through a portion of the sensor port and includes first and second ends disposed within the sensor port and the compressor outlet, respectively, and a curved section interposed between the first and second ends. The second tube includes a sleeve tightly fittable between the first end and the sensor port and a base. The base has an exterior surface from which the sleeve extends and which is disposed and configured to non-rotatably abut with an interior surface of the compressor outlet.

Abstract: A gas bearing within a cylinder is provided. The gas bearing comprises an anti-rotation tab sitting within a key way of the cylinder. Further, the gas bearing comprises a first foil forming an inner loop and an intermediary loop. The inner loop extends in a first direction from a first end to an intermediary portion. The intermediary loop extends from the intermediary to the anti-rotation tab.

Abstract: A turbine thrust shaft providing a thrust disk having a surface P and a surface Q, and a shaft body formed through the thrust disk, the shaft body including a first plurality of holes, wherein the first plurality of holes are spaced apart and each hole of the first plurality of holes has a first diameter between 0.0600 inches to 0.0680 inches and has a first center disposed a first distance between 0.1400 inches to 0.1600 inches from surface P, and a second plurality of holes wherein the second plurality of holes are spaced apart and each hole of the second plurality of holes has a second diameter between 0.0960 inches to 0.1040 inches and has a second center disposed a second distance between 2.1350 inches to 2.1550 inches from surface Q.

Abstract: A seal assembly of an air cycle machine includes a seal plate with an outer diameter. A bore extends axially through a center of the seal plate and a seal land is disposed at least partially within the bore. The seal land includes an inner diameter and a minimum ratio between the inner diameter of the seal land and the outer diameter of the seal plate is approximately 0.1985.

Abstract: A bleed assembly includes a bleed valve disposed across a bleed duct. The bleed valve includes a valve housing, a shaft connecting an actuator assembly to a flow control member, and a servo tube. The actuator assembly includes a linear actuator disposed perpendicular to a valve centerline, so that linear motion of the actuator is transverse to a valve centerline. The member is in the main fluid passage, rotatable between a fully closed position defined by leading and trailing edges abutting one or more housing walls, and a fully open position defined by the leading edge at the upstream side and the trailing edge at the downstream side of the main flow passage. A first portion of a servo tube extends into the main passage from a distance P1 upstream of the member in a fully closed position, and angular distance A1 of at least 10° from the TDC position.

Abstract: A gas bearing within a cylinder is provided. The gas bearing comprises an anti-rotation tab comprising a first side and a second side, the anti-rotation tab sitting within a key way of the cylinder. Further, the gas bearing also comprises a first foil extending in a first direction from a first end to the first side of the anti-rotation tab and a second foil extending in a second direction from a second end to the second side of the anti-rotation tab.

Abstract: A gas bearing within a cylinder is provided. The gas bearing comprises an anti-rotation tab sitting within a key way of the cylinder. Further, the gas bearing comprises a first foil forming an inner loop and an intermediary loop. The inner loop extends in a first direction from a first end to an intermediary portion. The intermediary loop extends from the intermediary to the anti-rotation tab.

Abstract: A compressor housing for an air cycle machine is provided. The compressor housing includes a body having a compressor volute configured to provide centrifugal compression in the air cycle machine. A mating surface is integrally formed with the body. The mating surface includes a plurality of substantially equally angularly spaced bosses. The bosses include a first boss type at a first radial distance and configured to receive a threaded fastener coupled to a turbine nozzle of the air cycle machine. The bosses also include a second boss type at a second radial distance configured to secure a seal plate of the air cycle machine. The second radial distance is less than the first radial distance. A ratio of a number of the bosses of the first boss type to the second boss type is 17 to 2.

Abstract: A piston assembly includes a piston with a first cap disposed on a first end of the piston and a second cap disposed on a second end of the piston. A piston cross-member is in between the first cap and the second cap. A first cover is affixed to a first side of the piston cross-member. A second cover is affixed to a second side of the piston cross-member. The second side of the piston cross-member is opposite the first side of the piston cross-member.

Abstract: A hydrodynamic thrust bearing has an annular plate, a plurality of bearing foils, and a plurality of bumper foils. The annular plate has a first face and a second face opposite the first face. The bearing foils have an arcuate shape and are joined to the first face of the annular plate. The bumper foils have an arcuate and corrugated shape and are joined to the second face of the annular plate. A method of making a hydrodynamic thrust bearing includes joining the bearing and bumper foils to the annular plate with integrally-formed spacers in which each bumper foil corresponds to a bearing foil.

Abstract: A bearing monitoring system is provided including one or more bearings within a flow passage and a working fluid passing over at least one surface of the bearings. A first thermocouple is located in the flow passage upstream relative to the one or more bearings and configured to measure a first temperature of the working fluid and a second thermocouple is located in the flow passage downstream relative to the one or more bearings and configured to measure a second temperature of the working fluid. The system further includes a control device in communication with the first thermocouple and the second thermocouple, and configured to compute a temperature gradient across the one or more bearings from the first temperature and the second temperature, compare the temperature gradient against a known value, and if the temperature gradient exceeds the known value, the control device is configured to provide an alert.

Abstract: An air cycle machine is provided. The machine includes a housing configured to enable airflow therethrough, a fan disposed within the housing and configured to rotate within the housing, and at least one aperture formed in the housing and configured to allow airflow through the at least one aperture from a cooling airflow path of an air cycle machine and into the housing. The at least one aperture is configured to optimally direct airflow passing therethrough toward the fan.

Abstract: An air cycle machine comprises rotating components that include a fan, a compressor, and a first turbine. The air cycle machine also includes a cooling airflow path that receives cooling air from a cooling air source, directs the cooling air to an air-cooled bearing for at least one of the rotating components, and discharges the cooling air. The airflow path is isolated from an inlet of the compressor by a seal member, and the airflow path is configured to maintain pressure at the seal member above a pressure at the compressor inlet.

Abstract: A self-acting pressure activated drain valve includes at least one inlet configured to receive a fluid. A drainage passage delivers the fluid to at least one outlet where the fluid is expelled. The self-acting pressure activated drain valve further includes a flexible diaphragm configured to operate in an open position and a closed position based on a pressure. The flexible diaphragm is normally biased in the open position such that fluid is delivered from the at least one inlet to the at least one outlet via the drainage passage. The pressure, however, initiates the closed position such that air is prevented from flowing through the drainage passage.

Abstract: An aircraft temperature control system to control a temperature of an environmental control system includes a ram inlet in fluid communication with an external area of the aircraft, and a ram outlet in fluid communication with an internal area of the environmental control system within the aircraft. A heat exchanger assembly is interposed between the ram inlet and the ram outlet. A ram air flow modulation valve is disposed downstream from the heat exchanger, and is configured to operate in a plurality of positions to regulate airflow delivered to the ram outlet. An electronic valve control module is in electrical communication with the ram air flow modulation valve and at least one temperature sensor. The electronic valve control module is configured to output an electrical signal that adjusts a position of the ram air flow modulation valve based on a temperature value output from the at least one temperature sensor.

Abstract: An embodiment of a valve includes a housing having at least an actuator chamber above a main fluid passage. A flow control member is mounted to a first longitudinal end of the valve shaft extending into, and is rotatable in, the main fluid passage. The linear actuator is retained in the actuator chamber, and includes a piston rod connected to at least one piston, and a slot formed transverse to a length of the piston rod. A yoke assembly includes a crank connected proximate to the second end of the valve shaft, A bearing assembly connecting the valve shaft and the piston rod includes at least one bearing connected to the crank such that the yoke assembly is adapted to translate linear motion of the piston shaft to rotational motion of the valve shaft, and vice versa.

Abstract: A quad foil journal air bearing includes a journal sleeve having an inner circumference that defines an inner surface. A first foil assembly includes a first key coupled to the inner surface of the journal sleeve. The quad foil journal air bearing further includes a second foil assembly having a second key coupled to the inner surface of the journal sleeve.