Airbus Operations Gmbh

Airbus Deutschland Gmbh

Jens Beier

Frank Klimpel

Alexander Solntsev

Johannes Eichholz

Ruediger Schmidt

Juergen Hintze

Thomas Uhlendorf

Matthias Geske

Stephan-Anton Schmidt

Michael Bielenberg

Michael Diesing-Jester

An air-conditioning system for an aircraft includes a compressed air branch for conveying externally supplied and pressurized air, preferably bleed air. Furthermore, a cooling circuit for conveying preferably liquid refrigerant is provided and extends through a ram air duct. The system also includes a first heat exchanger for the heat transfer between the compressed air branch and the cooling circuit, a compressed air turbine arranged in the compressed air branch and a cooling circuit compressor arranged in the cooling circuit and mechanically coupled to the compressed air turbine. The system can have a modular design and be positioned at optimal locations in the aircraft due to the separation of the compressed air branch and the cooling circuit. In this way, the length of hot compressed air ducts can be shortened.

Aircraft air conditioning system comprising a separate refrigeration cycle

A fresh air inlet for an aircraft features a ram air inlet with a ram air inlet opening, a secondary air inlet opening separate from the ram air inlet and a movably mounted flap. The flap can be moved into a first or second position, and essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and extends away from the aircraft body in the second position to shield the ram air inlet opening from foreign matter in the air. The secondary air inlet reduces the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. The ram air inlet can be optimized for cruising phases, and the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced.

Fresh air inlet for an aircraft

An apparatus for pressurizing an aircraft cabin structure and measuring the amount of leakage of the aircraft cabin structure comprises an air supply line which at a first end is connectable to a pressurized air source and which at a second end is connectable to the aircraft cabin structure so as to supply pressurized air from the pressurized air source into the aircraft cabin structure, an air supply valve disposed in the air supply fine, a pressure sensor for sensing the pressure inside the aircraft cabin structure and for providing signals indicative of the pressure inside the aircraft cabin structure, an air discharge line which at a first end is connectable to the aircraft cabin structure and which at a second end is connectable to an air discharge opening so as to discharge air from the inside of the cabin structure to the air discharge opening and an air discharge valve disposed in the air discharge line. An electronic control unit is adapted to control the air supply valve and the discharge valve in dependence on signals provided by the pressure sensor.

Apparatus and method for pressurising an aircraft cabin structure and measuring the amount of leakage of the aircraft cabin structure

The invention relates to a device () for heating an aircraft cabin and comprises a first hot air supply line () that leads to an air conditioning unit (), a flow control valve () that is disposed in the first hot air supply line () upstream from the air conditioning unit (), and a second hot air supply line () that branches off from the first hot air supply line () between the flow control valve () and the air conditioning unit () and bypasses the air conditioning unit (). In order to assure air conditioning of the aircraft cabin in the event of a failure of the air conditioning unit () a third hot air supply line () branches off from the first hot air supply line () upstream from the flow control valve (), which third hot air supply line () connects the first hot air supply line () to the second hot air supply line (). Further a first close off mechanism is disposed in the second hot air supply line () upstream from the junction with the third hot air supply line (), which first close off mechanism in its closed position prevents a flow from the second hot air supply line () back into the first hot air supply line (). Finally a second close off mechanism is disposed in the third hot air supply line () upstream from the junction with the second hot air supply line ().

Device and process for heating an aircraft cabin

Growing community of inventors

Drestedt, Germany

Jens Beier