A ventilation assembly comprises a number of fan systems configured to purify air and a number of air distribution assemblies. Each air distribution assembly of the number of air distribution assemblies is configured to be removably installed on a seatback of a passenger seat. Each air distribution assembly of the number of air distribution assemblies comprises a pair of air distribution vents, ductwork configured to receive air from at least one fan system of the number of fan systems and direct air to the pair of air distribution vents, and a seat attachment device configured to removably couple the pair of air distribution vents to the seatback such that each air distribution vent is situated on opposite sides of the seatback for providing purified air to a seated passenger.

A cooling arrangement for a kitchen provided for installation in a means of transport comprises a cooling circuit which can have a cooling medium flowing through it and in which a condenser and an evaporator are arranged. The condenser is accommodated in a condenser housing and is arranged in a first installation space which is intended to form a first sub-region of the kitchen. The evaporator is accommodated in an evaporator housing formed separately from the condenser housing, and is arranged in a second installation space which is intended to form a second sub-region of the kitchen.

A cooling arrangement for a kitchen provided for installation in a means of transport comprises a cooling circuit which can have a cooling medium flowing through it and in which a condenser and an evaporator are arranged. The condenser is accommodated in a condenser housing and is arranged in a first installation space which is intended to form a first sub-region of the kitchen. The evaporator is accommodated in an evaporator housing formed separately from the condenser housing, and is arranged in a second installation space which is intended to form a second sub-region of the kitchen.

An aircraft environmental control system comprising a fresh air input and a RAM air input, heat exchanger means for receiving fresh air from the fresh air input and RAM air from the RAM air input and using the RAM air to cool the fresh air, and means for providing the cooled fresh air to a cabin of the aircraft, the system further comprising means for feeding back exhaust air emitted from the interior of the aircraft to combine with the RAM air to further cool the fresh air, whereby the heat exchanger means comprises a main heat exchanger and a primary heat exchanger; wherein the main heat exchanger comprising a main heat exchanger cooling fluid inlet, a main heat exchanger cooling fluid outlet and a main heat exchanger bleed air inlet, the cooling fluid working to cool bleed air in the main heat exchanger.

An aircraft environmental control system comprising a fresh air input and a RAM air input, heat exchanger means for receiving fresh air from the fresh air input and RAM air from the RAM air input and using the RAM air to cool the fresh air, and means for providing the cooled fresh air to a cabin of the aircraft, the system further comprising means for feeding back exhaust air emitted from the interior of the aircraft to combine with the RAM air to further cool the fresh air, whereby the heat exchanger means comprises a main heat exchanger and a primary heat exchanger; wherein the main heat exchanger comprising a main heat exchanger cooling fluid inlet, a main heat exchanger cooling fluid outlet and a main heat exchanger bleed air inlet, the cooling fluid working to cool bleed air in the main heat exchanger.

An air supply system for a pneumatic de-icing assembly for de-icing surfaces of an aircraft, the aircraft comprising an air-conditioning system supplied by at least one first air compressor connected to a device for drawing in air outside the aircraft, the pneumatic de-icing assembly comprising an air supply inlet connected to an outlet of the first air compressor or to an outlet of the air-conditioning system. Thus, it is possible to supply air to a pneumatic de-icing system of an airplane equipped with electric motors or of what is referred to as “bleedless” type.

An air supply system for a pneumatic de-icing assembly for de-icing surfaces of an aircraft, the aircraft comprising an air-conditioning system supplied by at least one first air compressor connected to a device for drawing in air outside the aircraft, the pneumatic de-icing assembly comprising an air supply inlet connected to an outlet of the first air compressor or to an outlet of the air-conditioning system. Thus, it is possible to supply air to a pneumatic de-icing system of an airplane equipped with electric motors or of what is referred to as “bleedless” type.

A water extractor for an environmental control system of an aircraft includes a separation mechanism configured to divide an airflow into a first airflow and a second airflow. The separation mechanism includes an inlet conduit, a body in fluid communication with the inlet conduit, and at least one coalescing feature arranged within an interior of the body. A water extraction vessel is arranged in fluid communication with the separation mechanism. The water extraction vessel includes a first portion for receiving the first airflow and a second portion for receiving the second airflow. The first portion is configured to collect and remove water from the first airflow.

A water extractor for an environmental control system of an aircraft includes a separation mechanism configured to divide an airflow into a first airflow and a second airflow. The separation mechanism includes an inlet conduit, a body in fluid communication with the inlet conduit, and at least one coalescing feature arranged within an interior of the body. A water extraction vessel is arranged in fluid communication with the separation mechanism. The water extraction vessel includes a first portion for receiving the first airflow and a second portion for receiving the second airflow. The first portion is configured to collect and remove water from the first airflow.

An overhead flow distribution assembly for an aircraft cabin, including a conduit defining a plenum having an inlet, upper outlets and lower outlets, the upper outlets spaced apart from each other along a longitudinal direction of the aircraft, the lower outlets spaced apart from each other along the longitudinal direction, the inlet being located between the upper outlets and the lower outlets, and a baffle extending within the plenum along the longitudinal direction, the baffle being located between the upper outlets and at least part of the inlet along a transverse direction normal to the longitudinal direction, the baffle having openings defined therethrough, the baffle configured to restrict airflow from the at least part of the inlet toward the upper outlets. A method of balancing a flow in an overhead flow distribution assembly for an aircraft cabin is also discussed.