The disclosure describes a system that includes an auxiliary power unit (APU), an APU throttle valve, and an environmental control system (ECS) bypass valve. The APU is configured to receive cabin discharge air from an aircraft cabin and receive ECS supply air from an air pressurization system (APS). The APU throttle valve is configured to control flow of cabin discharge air from the cabin to the APU. The ECS bypass valve configured to control flow of ECS supply air from the APS to the APU.

A flatpack air chiller device is disclosed. In embodiments, the air chiller device includes a primary chiller or pre-chiller subsystem and a secondary or main chiller subsystem within a housing. The pre-chiller subsystem receives and chills ambient air via cold-side contact with a primary thermoelectric device and directs the pre-chilled ambient airstream to the hot side of a secondary thermoelectric device. The secondary or main chiller subsystem is connected to a recirculating air stream, e.g., circulating through the interior airspaces, compartments, or bays of a galley structure. The pre-chilled ambient airstream absorbs heat from the secondary hot side to progressively chill the recirculating air stream, which is in contact with the cold side of the secondary thermoelectric device before recirculation back into the galley structure interior.

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.

An air cycle machine includes a compressor in fluid communication with a load cooling heat exchanger, a first valve and a first turbine connecting the compressor to the load cooling heat exchanger, and a second valve and a second turbine. The second valve and the second turbine connect the compressor to the load cooling heat exchanger and connected in parallel with the first valve and the first turbine between the compressor and the load cooling heat exchanger. Air cycle machine systems and methods of controlling air flow through air cycle machines are also described.

A duct is provided and includes a tubular member having an inlet portion, an outlet portion and a central portion interposed between the inlet and outlet portions and a tributary tubular member fluidly coupled to the tubular member at the central portion. The tributary tubular member includes first and second torus sectors defining first and second apertures, respectively, through which an upstream end of the central portion extends. The second torus sector is disposed within the first torus sector to define a sectioned toroidal annulus about the first and second apertures and between an exterior surface of the second torus sector and an interior surface of the first torus sector.

A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine. The first medium is provided to the compressor and the turbine sequentially. A second medium is provided to the environmental control system. In a first mode of operation, the first medium and the second medium mix within the turbine and in a second mode of operation the second medium bypasses the turbine such that the first medium and the second medium mix downstream from the turbine.

Cabin outflow temperature control systems and methods for use on aircraft are described. The systems include an aircraft cabin, a heat load source, a heat exchanger configured to receive cabin outflow air from the aircraft cabin and heat load discharge air, the heat exchanger configured to enable thermal transfer from the heat load discharge air to the cabin outflow air to generate high temperature cabin outflow air and low temperature discharge air as outputs from the heat exchanger, and one or more downstream operation systems configured to receive the high temperature cabin outflow air and perform a downstream operation using said high temperature cabin outflow air.

An environmental control system includes a compression device including a compressor, a turbine, and an electric motor operably coupled by a shaft. The electric motor and the turbine are arranged in series relative to a flow of a first medium.

An insert for an air intake of a suction duct, the insert including an inner portion configured to extend within the suction duct, a mating portion configured for sealingly engaging the air intake, and an outer portion configured for extending outside of the suction duct. The inner portion includes a conduit having a central axis extending along an inlet direction at the inlet end and along an outlet direction at the outlet end, the inlet and outlet directions being non-parallel. The outlet end has a smaller cross-sectional area than that of the suction duct. The insert includes an inlet in fluid communication with the inlet end of the conduit. The outer portion includes a curved lip surrounding at least part of an inlet opening of the inlet, the lip configured to direct a flow into the inlet opening and toward the inlet end of the conduit.

Aircraft systems including a pressurized fuel tank containing a pressurized fuel, a turbo expander configured to receive the pressurized fuel from the fuel tank, the turbo expander configured to decrease a pressure of the pressurized fuel to generate low pressure fuel having pressure less than the pressurized fuel, a fuel-to-air heat exchanger configured to receive the low pressure fuel from the turbo expander as a first working fluid and air as a second working fluid, the heat exchanger configured to cool the air and warm the fuel, an aircraft cabin configured to receive the cooled air, and a fuel consumption system configured to consume the fuel to generate power.