An ozone converter includes an outer housing having an inlet and an outlet, a first channel disposed between the inlet and the outlet, and a bypass channel disposed between the inlet and the outlet and separated from first channel. The converter also includes a core disposed within the first channel and a bypass control mechanism that includes one more blocking elements that causes inlet air to pass through the first channel or the bypass channel based on an altitude of the ozone converter. The control mechanism includes a piston that moves between at least a first position and a second position and a bellows that controls a flow a pressurized air to the piston.

Ozone converters containing differing ozone converting materials are provided into air aircraft airflow management systems, with the ozone converter positioned in an air management architecture at positions configured to assist replacement, and maintenance, and with the ozone converters further positioned downstream of air conditioning packs, and with the ozone converters configured to reduce at least one of ozone concentrations and volatile organic compound concentrations from airflows directed to passenger cabin air volumes and flight deck air volumes.

A mixer assembly for mixing two air streams in a ventilation system. The mixer assembly comprises a mixing chamber, which comprises an inlet and an outlet and a mixing chamber wall delimiting the mixing chamber, and also a shroud, which surrounds the mixing chamber wall, at least in certain portions. The shroud forms and delimits an intermediate space between the mixing chamber wall and the shroud. The mixer assembly also comprises a filter element, which fluidically connects the intermediate space to a surrounding area of the mixer assembly, the intermediate space being fluidically connected to the mixing chamber. Fluid can thus flow through the filter element into the intermediate space and further into the mixing chamber. A stowage space with a mixer assembly, an aircraft with such a stowage space and a method for producing a mixer assembly in an aircraft are also described.

A compact lightweight air filtration system is disclosed. The air filtration system includes a hydrophobic particulate/coalescing filter and a cleanable ozone converter housed in a housing with an inlet and an outlet. Air flowing from the inlet to the outlet passes through the particulate/coalescing filter element and then the cleanable ozone converter to remove particulates, aerosols, liquids, and ozone. The air filtration system may comprise a fuel tank inerting system (FTIS) filter assembly. The FTIS filter assembly may include a binderless media (no binder) suitable for use in high temperatures. The FTIS filter assembly includes a catalytic converter configured to adsorb one or more VOCs, such as Toluene, Propylene Glycol (C.sub.3H.sub.8O.sub.2), Pentanoic Acid, Butane (C.sub.4H.sub.10), Formaldehyde (CH.sub.2O), and Carbon Dioxide (CO.sub.2).

A filter assembly including a plurality of filter modules, wherein each filter module in the plurality of filter modules includes a frame, a filtration element coupled within the frame, and at least one mating feature. The at least one mating feature of each filter module is configured for selective engagement with the at least one mating feature of another filter module such that the plurality of filter modules are coupled together in a serial arrangement.

An apparatus is disclosed that includes an aircraft or repurposed aircraft or fuselage having a cabin capable of pressurization, a way to pressurize the cabin whether by built in machinery or external apparatus, a way to deliver oxygen to a plurality of persons in the cabin, a source of hyperbaric oxygen, a pressure gauge or regulator configured to measure or regulate a pressure of the hyperbaric oxygen or the aircraft, a plurality of face or head coverings configured to provide the hyperbaric oxygen to persons or patients in need thereof, and an optional exhaust system configured to remove gas(es) from the face or head coverings without releasing the gas(es) into the cabin. Each of the face or head coverings includes a gas inlet, a gas outlet, and one or more seals adapted to contain oxygen in the face or head covering at a pressure greater than 1 atm. A related kit and a related method of treating persons with hyperbaric oxygen are also disclosed.

A method of recovering performance of an air separation module (ASM) is described. A recovery system includes an air source providing inlet air, a filter to output clean air and a heater heating the air. The ASM is coupled to the system and comprises a hollow fiber membrane to output nitrogen enriched air (NEA) exhaust. The method comprises operating the system with the air source and heater in a default condition; measuring an initial purity of NEA exhaust; adjusting the air source and/or heater based on the initial purity; operating the system after adjusting the air source and/or heater; returning the air source and heater to the default condition; measuring a recovered purity of NEA exhaust; and determining whether the recovered purity is within tolerance. If the recovered purity is within tolerance, system operation is terminated. If the recovered purity is not within tolerance, the steps are repeated.

A compact lightweight air filtration system is disclosed. The air filtration system includes a hydrophobic particulate/coalescing filter and a cleanable ozone converter housed in a housing with an inlet and an outlet. Air flowing from the inlet to the outlet passes through the particulate/coalescing filter element and then the cleanable ozone converter to remove particulates, aerosols, liquids, and ozone.

A system comprises an ozone conduit in fluid communication with an aircraft door seal configured to seal the ozone conduit to an aircraft door. An ozone source is in fluid communication with the ozone conduit for supplying a flow of ozone gas (O.sub.3) to an aircraft interior through the ozone conduit and aircraft door seal. The ozone conduit can be an ozone inlet line, and an ozone outlet line can be in fluid communication with the aircraft door seal for removal of ozone from the aircraft interior.

An environmental control system of an aircraft includes a ram air circuit with a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, a compression device arranged in fluid communication with the ram air circuit and the at least one dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit. At least one of the compression device and the expansion device is selectively operable to supplement the ram air within the ram air circuit to meet a demand of the aircraft.