An air conditioner and an air guide for an air conditioner are provided, the air guide being configured to guide air to a cross-flow fan of the air conditioner. The air conditioner may include a case including a front panel and a rear panel, the front panel including an intake grill and an outlet, a cross-flow fan and a heat exchanger being disposed inside of the case. The rear panel may include an air guide. The air guide may include a first guide surface inclined toward the cross-flow fan, and a second guide surface positioned at a downstream side of the first guide surface. The first guide surface may include at least one distribution guide that distributes and guides air, and thus, the air having been equally distributed by means of the at least one distribution guide may be suctioned into the cross-flow fan so that vortex generation is prevented, thereby enabling noise to be reduced.

An assembly is provided for an aircraft propulsion system. This assembly includes a variable area inlet. The variable area inlet includes a moveable structure configured to move axially along an axial centerline between a first position and a second position. The variable area inlet is configured to open an airflow inlet passage into the aircraft propulsion system when the movable structure is in the first position. The variable area inlet is configured to close the airflow inlet passage when the movable structure is in the second position. The airflow inlet passage includes an inlet. The inlet extends axially along the axial centerline from a first end to a second end. A distance from the first end to the second end changes as the inlet extends laterally between a first side and a second side.

A propulsion system is provided including an unducted rotating fan defining a fan axis; and a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough; wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine.

A centrifugal compressor for a chiller system includes a casing having an inlet portion and an outlet portion, a recirculation structure including a recirculation path and a recirculation discharge cavity, an impeller disposed downstream of the recirculation discharge cavity, a plurality of recirculation discharge guide vanes disposed to surround the recirculation discharge cavity, and a diffuser disposed in the outlet portion downstream of the impeller. The recirculation structure is configured to impart a swirl to a flow of refrigerant into the inlet portion. The recirculation path supplies the refrigerant from the diffuser to the recirculation discharge cavity. The recirculation path includes a recirculation pipe that introduces the refrigerant toward the plurality of recirculation discharge guide vanes. An annular groove is disposed between the recirculation pipe and the plurality of recirculation discharge guide vanes. An annular plate is disposed between the annular groove and the recirculation discharge cavity.

A radial compressor having a specially designed iris diaphragm mechanism is described. This mechanism includes only a single (main) blade that is driven directly by an actuating element, while the other blades are driven by the respective preceding blade via the movement of the main blade. This results in a particularly simple embodiment of the iris diaphragm mechanism. A blade for an iris diaphragm mechanism of this type and a charging device having a radial compressor of this type are furthermore described.

A portable system is disclosed for collecting a sample from exhaled breath of a subject. Drug substance in the exhaled breath are detected or determined. The sample is collected for further analysis using mass-spectroscopy. The system comprises a sampling unit and a housing arranged to hold the sampling unit, the sampling unit is adapted to collect non-volatile and volatile compounds of the at least one drug substance from the exhaled breath from the subject. The housing has at least one inlet for the subject to exhale into the housing to the sampling unit and at least one outlet for the exhaled breath to exit through.

A blower in one aspect of the present disclosure includes: a housing including a suction port and a discharge port; a motor in the housing; a fan in the housing; a motor drive circuit; and a control circuit. The control circuit detects an insufficient airflow from the suction port to the discharge port based on an operation parameter. The operation parameter is associated with an operation of the motor.

A centrifugal compressor of an aircraft engine includes an impeller and a shroud extending circumferentially around the impeller. A bellmouth disposed upstream of the impeller extends circumferentially and includes: a conduit section extending from a first end to an upstream-most location of the bellmouth, the first end of the conduit section secured to the shroud, and a peripheral section extending from the upstream-most location to a second end located radially outwardly of the first end, the peripheral section located radially outwardly of the conduit section and axially overlapping the conduit section. A stiffening member is located on the peripheral section of the bellmouth proximate the second end. The stiffening member extends circumferentially and provides the bellmouth with a dynamic vibration mode outside a range of dynamic vibration modes of the aircraft engine during operation.

A compressor has a rotor assembly having an impeller for generating an airflow through the compressor, a stator core assembly for causing rotation of the impeller, and a diffuser assembly for acting on the airflow generated by the impeller. The diffuser assembly has a first diffuser stage and a second diffuser stage. The first and second diffuser stages are separate components connected to one another by a fastener.

A method of reducing low-energy flow in a flight vehicle engine includes an isolator of the engine having a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.