A water separation mechanism includes a housing having a hollow interior, an inlet and an outlet, and a center body arranged within the hollow interior. A plurality of coalescing features are mounted about a periphery of the center body in a plurality of stages. The plurality of stages are arranged in series relative to a direction of an airflow through the housing. The plurality of coalescing features are configured to separate the airflow into a wet first airstream and a dry second airstream.

A variable chiller exhaust system incorporate a plurality of chillers, each driller having an inlet receiving air from a crown in an aircraft fuselage and an outlet connected to a manifold. A plurality of check valves are connected to the manifold and configured to maintain a differential back pressure on the plurality of chillers of 2″ water pressure or less. The check valves vent into the crown. An exhaust conduit is connected to direct air from the manifold to a variable speed fan. An outflow valve exhausts air from the variable speed fan to an exterior of the fuselage.

A water extractor for use in an environmental control system, the water extractor comprising a housing having an inlet end and an outlet end, a swirling mechanism mounted within the housing, and a fog harvester assembly mounted within the housing at a location between the inlet end and the outlet end.

A humidification device is provided with at least one stacked unit with water vapor-permeable membranes arranged parallel and spaced apart relative to each other. The membranes each have an edge area framed by frames. The frames are formed by a film composite of a lower film and an upper film, wherein the lower and upper films of the film composite clamp the edge area of one or more of the membranes therebetween. The lower and upper films of the film composite are fixedly connected to each other. Alternatively, the frames are formed by a thermoplastic yarn that is sewn into the edge area of one or more of the membranes, respectively, wherein the thermoplastic yarn is reshaped by heat and pressure.

A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a heat exchanger configured to receive the compressed air from the compressor and cool the compressed air; a turbine configured to receive the cooled air from the heat exchanger, with the cooled air expanding as the cooled air flows through the turbine. Furthermore, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, at least a portion of the cooled air from the heat exchanger is routed to the defroster to melt the captured frozen particulate matter.

A fluid system includes an inlet conduit disposed in a fluid flow path between a fluid source and a fluid destination. The fluid conduit includes a fluid mixing portion. The fluid system includes a fluid separation module disposed in the flow path downstream of the constriction between the source and the destination. The fluid separation module includes a first fluid separator, The fluid system includes a second fluid separator disposed in the flow path upstream of the first fluid separator, The fluid system includes a feedback conduit that may provide fluid communication between an outlet of the fluid separation module and the fluid mixing portion.

An aircraft includes a cooling compartment and an evaporative chiller configured to cool the cooling compartment. The evaporative chiller includes a compressor, an evaporator having airflow to the cooling compartment, and a condenser. The condenser has an exhaust airflow to cool the condenser. The evaporative chiller has a condensate removal system removing condensate produced by the evaporator using the exhaust airflow of the condenser to discharge the condensate.

A environmental control system (ECS) for an aircraft includes a primary heat exchanger configured to receive bleed air from a turbine compressor of the aircraft and a secondary heat exchanger having an input configured to receive a flow from the primary heat exchanger and a secondary heat exchanger output. The ECS also includes a thermoelectric condensing device having an input in fluid communication with the output of the secondary heat exchanger and also having a thermoelectric condensing device output.

Air conditioning system for a cabin (10) of an aircraft, comprising: an air bleed device; an air cycle turbine engine (12); at least one main cooling exchanger (16); a water extraction loop (30); and a pipe (26) for distributing water extracted by said extraction loop (30), characterized in that said system further comprises means (40) for heating the water extracted by the water extraction loop so as to be able to spray the water into a ram-air channel (22) which supplies said main exchanger (16).

Nebulizer systems to generate a mist of micro-droplets of a liquid for the purpose of freshening the atmosphere. Nebulizer systems having a small size that can be mounted on a sales stall to humidify and freshen fresh products displayed for sale, or in a vehicle to humidify and freshen the air and make it pleasant to breathe.