A variable chiller exhaust system incorporate a plurality of chillers, each chiller 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.

Vehicles, humidification systems for a vehicle, and methods for humidifying an interior of a vehicle are provided. In one example, the vehicle includes a vehicle structure at least partially surrounding an interior containing interior air. A humidification system is in fluid communication with an air stream and the interior. The humidification system includes a humidifier configured to humidify the air stream to form a humidified air stream that is fluidly communicated to the interior. A water recovery zone is in fluid communication with the interior to receive the interior air and is configured to condense and separate water from the interior air. The water recovery zone is further configured to be in fluid communication with the humidifier and to provide the water to the humidifier.

Vehicles, humidification systems for a vehicle, and methods for humidifying an interior of a vehicle are provided. In one example, the vehicle includes a vehicle structure at least partially surrounding an interior containing interior air. A humidification system is in fluid communication with an air stream and the interior. The humidification system includes a humidifier configured to humidify the air stream to form a humidified air stream that is fluidly communicated to the interior. A water recovery zone is in fluid communication with the interior to receive the interior air and is configured to condense and separate water from the interior air. The water recovery zone is further configured to be in fluid communication with the humidifier and to provide the water to the humidifier.

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.

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 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.

An example temperature sensing device includes an air distribution inlet through which primary air is blown into via an environmental control system, a cabin air inlet through which secondary air enters from a passenger area of a fuselage and the cabin air inlet is coupled to the air distribution inlet through a duct and the secondary air is passively drawn into the cabin air inlet and to the duct due to a pressure difference present in the duct, and a temperature sensor coupled to the duct and positioned downstream of the cabin air inlet along an airflow path of the secondary air so as to be exposed to the secondary air drawn in through the cabin air inlet and flowing through the duct.

An example temperature sensing device includes an air distribution inlet through which primary air is blown into via an environmental control system, a cabin air inlet through which secondary air enters from a passenger area of a fuselage and the cabin air inlet is coupled to the air distribution inlet through a duct and the secondary air is passively drawn into the cabin air inlet and to the duct due to a pressure difference present in the duct, and a temperature sensor coupled to the duct and positioned downstream of the cabin air inlet along an airflow path of the secondary air so as to be exposed to the secondary air drawn in through the cabin air inlet and flowing through the duct.

Heat exchanger assembly comprising a ram air flow channel (14) extending in a longitudinal direction, and characterized in that said assembly comprises: at least two separate heat exchangers (12a, 12b) that are adjacent in a transverse direction perpendicular to the longitudinal direction, are arranged in the ram air flow channel (14), and are configured such that the ram air passing through said channel (14) forms a cold pass of each heat exchanger (12a, 12b) by passing through said heat exchanger (12a, 12b) in said longitudinal direction, each heat exchanger (12a, 12b) also being configured for the passage therethrough of a fluid that is intended to be cooled and that forms a hot pass (20a, 20b); and an air passage which is provided between the heat exchangers and forms a thermally insulating air gap (18) between said exchangers (12a, 12b), and through which the ram air flows, said air passage extending in said longitudinal direction of said ram air flow channel (14).

A cabin blower for an aircraft, the system comprising: a cabin blower compressor; an electric machine; and a controller configured to control the cabin blower system so that: in a cabin blower mode of operation, the cabin blower compressor is driven by power extracted from one or more spools of a gas turbine engine of the aircraft and provides a flow of air to a cabin of the aircraft. The controller may be further configured to control the system so that: in a rotor bow mitigation mode of operation, the cabin blower compressor is driven by the electric machine using electrical power from an electrical power source and provides a flow of air through a core of the gas turbine engine to remove heat from the core. A method of operating a cabin blower system of an aircraft is also provided.