A method and system for controlling fresh air flow into a controlled environment are disclosed herein. The method comprises: measuring, using a sensor, a predetermined property in the controlled environment; estimating, by a controller, a number of people inside the controlled environment based on the measured property, and setting, by the controller, a rate of fresh air flow to the controlled environment based at least in part on the estimated number of people inside the controlled environment.

A method of retrofitting an environmental control system of an aircraft includes inserting the orifice plate through the connector slot and the connector ring slot into the receptacle. The method also includes aligning the covering portion with the connector slot.

Pneumatic air systems for use onboard aircraft include a compressor configured to receive air from an air supply and increase a pressure of said received air to generate compressed air, a heat exchanger configured to receive the compressed air as a first working fluid and a treating air as a second working fluid, the heat exchanger configured to convert the compressed air to compressed and temperature treated air, one or more aircraft systems configured to receive the compressed and temperature treated air, and a surge prevention circuit arranged to prevent surge of air at the compressor, wherein the surge prevention circuit comprises a mechanical valve that is actuated based on a detected pressure within a sense line operably coupled to the mechanical valve.

A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.

Described herein are noise attenuating ducts and vehicles using these ducts for environmental control systems. A duct comprises an exoskeleton structure and a sound-absorbing structure, disposed within and conforming to the exoskeleton structure. The exoskeleton structure provides external mechanical support to the sound-absorbing structure thereby helping to maintain the tubular shape of the sound-absorbing structure. This external support does not interfere with the airflow inside the sound-absorbing structure. Furthermore, the external positioning of the exoskeleton structure allows the integration of various support mounting features for the installation of the duct in a vehicle. In some examples, the exoskeleton structure comprises a plurality of enclosed openings to reduce the weight of the exoskeleton structure and provide additional flexibility. Furthermore, additive manufacturing of the exoskeleton structure allows achieving a monolithic structure with various features and characteristics described above.

A disinfecting system and method for an enclosed space include an articulating arm moveably coupled to a structure within the enclosed space. An ultraviolet (UV) lamp is coupled to the articulating arm. The UV lamp is configured to emit UV light toward a disinfection zone within the enclosed space. The articulating arm allows the UV lamp to move relative to the disinfection zone.

An environmental control system of an aircraft including a compression device including a compressor having a compressor inlet and a compressor outlet, a primary inlet for supplying a first medium to the compressor inlet, and a secondary inlet for supplying a second medium to the compressor inlet.

An air supply system comprising at least two bleed sources configured to provide bleed air, wherein each bleed source comprises an engine or an auxiliary power unit and an oil as lubricant for the engine or the auxiliary power unit. The system also includes at least one air conditioning pack for cooling the bleed air from the bleed sources, and a plurality of bleed ducts, wherein each bleed duct connects one of the bleed sources to the at least one air conditioning pack. The system further comprises a plurality of detectors, wherein each detector is associated with a bleed source and the plurality of detectors are configured for detecting substances specific for the oil.

An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

A microtube heat exchanger is disclosed, including two end plates with an array of holes or openings and an array of microtubes disposed in the array of openings between the two end plates. The heat exchanger can be used in environmental control systems, including systems for aerospace applications.