Airbus Deutschland Gmbh

Daimlerchrysler Aerospace Airbus Gmbh

Airbus Operations Gmbh

Airbus (sas)

Uwe Buchholz

Thomas Scherer

Michael Markwart

Juergen Kelnhofer

Ingo Gores

Hans-Joachim Scheffler

Dariusz Krakowski

Jan Dittmar

Carsten Colberg

Nico Centofante

Markus Petrac

Nicolas Antoine

Marcus Petrac

Peggy Bendfeldt

Christina Kopp

Christina Koepp

Peggy Benfeldt

Michael Heesch

Christina Köpp

A system for air conditioning at least one partial region of an aircraft includes an air providing device for providing air to be supplied to a region of the aircraft to be ventilated at a desired temperature and pressure. A supply air duct is connected at a first end to the air providing device. A second end of the supply air duct is connected to an air inlet which opens near the floor into the aircraft region to be ventilated. A control device is set up to ensure that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a speed that the air is distributed near the floor in the aircraft region to be ventilated and rises at heat sources present in the aircraft region to be ventilated.

System and method for air conditioning at least one partial region of an airplane

A system for air conditioning at least one partial region of an aircraft comprises an air providing device for providing air to be supplied to a region of the aircraft to be ventilated at a desired temperature and pressure. A supply air duct is connected at a first end to the air providing device. A second end of the supply air duct is connected to an air inlet which opens near the floor into the aircraft region to be ventilated. A control device is set up to ensure that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a speed that the air is distributed near the floor in the aircraft region to be ventilated and rises at heat sources present in the aircraft region to be ventilated, and that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a temperature that a desired ambient temperature is set in the aircraft region to be ventilated.

An energy supply system for operating at least one air conditioning system of an aircraft, comprises at least one air line network and at least one electric line network. The air line network is connected to the air conditioning system and at least one bleed air connection for routing bleed air to the air conditioning system. The electric line network is connected to the air conditioning system and at least one electrical energy source for routing electrical energy to the air conditioning system. The air conditioning system has an electrically operable cooling device. By means of the energy supply system according to the invention the energy withdrawn from the power units is better adapted to the energy necessary for operating the air conditioning system and other systems&#x2014;such as, for example, wing de-icing&#x2014;and therefore reduces the excess fuel consumption of the aircraft.

Air conditioning system with hybrid mode bleed air operation

A device for temperature control in an aircraft cabin includes a first supply control arrangement and a first pressure control arrangement. The first supply control arrangement includes an air duct and a valve arrangement that controls a supply of heated air delivered to a first temperature area of the aircraft cabin such that a first specified temperature for the first temperature zone is achieved. When the valve arrangement fails, the first pressure control arrangement operates to control a pressure of heated air supplied into the first temperature area such that the first specified temperature for the first temperature zone is achieved.

Device and method for temperature control in an aircraft cabin

A device for mixing fresh air and heating air in a ventilation system of an aircraft includes a fresh air inlet, a heating air supply body for supplying the heating air into the device, and a mixed air outlet for delivering mixed fresh air and heating air from the device. The heating air supply body includes a first portion and a second portion which constitute a flow resistance to the fresh air. The second portion is formed as a closed hollow body with a plurality of heating air supply openings and is connected to the first portion at a downstream end of the first portion, viewed in the flow direction of the heating air. Advantageously, the first portion of the heating air supply body is of streamlined shape.

Device for mixing fresh air and heating air and use of the device in a ventilation system of an aircraft

Aircraft fuselage with an upper deck, constructed as a passenger area, and a lower deck, including a freight area, and with a ventilation installation for the upper deck and lower deck, wherein a bilge area is constructed as a vacuum chamber against the freight area and is connected to the lower deck solely via flow orifices in the abutment area between a lower floor and the fuselage wall.

Aircraft fuselage with upper and lower deck

An air discharge valve for an aircraft has an inner valve flap () and an outer valve flap () which partially overlap each other to form a nozzle of the Laval type with a nozzle inlet () converging toward a nozzle neck (S) and with a nozzle outlet () diverging away from the nozzle neck (S). The inner valve flap () has a trailing edge (A) hinged to the aircraft body and a first leading edge () facing in the flight direction and having a curved sectional configuration. The outer valve flap () has a second leading edge () hinged to the aircraft body and a trailing edge (A). Both flaps () have a wedge shape. An outwardly facing surface portion (B) of the inner flap () forms an air flow guide for air flowing out of the nozzle outlet (). An inwardly facing surface portion (B) of the outer flap () forms an air flow guide into the nozzle inlet () formed by the curved sectional configuration of the first leading edge () and by the inwardly facing surface portion (B).

Air discharge valve for an aircraft

An air mass or volume flow in an aircraft is controlled in a closed loop control system. A controllable air distribution network is formed by pipes, ducts, valves, fans, a fresh air supply and climate packs. The generation of a closed loop control signal is based on a continuous recalculation or updating of rated performance characteristic data with regard to current pressure, temperature and altitude data. The updated data are compared with actually measured current data to produce the control signal. The rated performance characteristic data are stored in a memory connected to a corrected (32) which also receives the current data. The sensing ascertains one or more temperature, pressure, altitude and flow volume data to Provide current actually measured data which are then compared with the updated data for generating the closed loop control signal for at least certain of the valves, fans, and fresh air supply.

Method and system for controlling an air mass flow in an aircraft

A cooling air arrangement for an aircraft air conditioning unit includes an air inlet, a heat exchanger, an outlet plenum, first and second air outlet channels branching from the plenum, and a fan arranged in the first outlet channel. During flight of the aircraft, external ram air driven into the air inlet flows primarily through the second outlet channel. During ground operation, the fan primarily sucks cooling air through the first outlet channel, which merges back into the second outlet channel at an air mixing junction that functions as an injector nozzle and a non-return flap valve. The first outlet channel is provided in a spiral housing of the fan, or in a smooth curved duct. The air inlet and outlet of the cooling air arrangement, and the air outlet of the air cycle machine, are oriented in the same direction, e.g. the flight forward direction.

Cooling air arrangement for a heat exchanger of an aircraft air conditioning unit

An air conditioning system for an aircraft includes a first rotatable shaft with a first compressor, a first turbine, a cooling air fan, and an auxiliary compressor connected for rotation therewith, and preferably further includes a second rotatable shaft with a second compressor and a second turbine connected for rotation therewith. A compression, cooling, and expansion cycle driven by at least the first compressor and the first turbine provides a principle flow of air conditioning air. The auxiliary compressor draws in outside air and provides a redundant auxiliary ventilation air flow, which is supplied into the installation space in which the air conditioning unit is installed, or another space in the aircraft that requires a reliable constant ventilation and cooling whenever the air conditioning unit is operational. The auxiliary ventilation air may be connected to a common air distribution network with other air conditioning units.

Aircraft air conditioning system providing auxiliary ventilation

In an air conditioning system for an aircraft, two pre-mixing units respectively mix cold air from two air conditioning units with recirculated fuselage interior air from two recirculation units, to prepare two pre-mixed air flows that are both directed into and mixed together in a common air distribution mixing chamber, from which mixed air distribution lines branch off to respectively associated separate air conditioning zones within the fuselage. Post-mixing units are respectively interposed in the mixed air distribution lines and respectively mix additional quantities of recirculated fuselage interior air into the mixed air distribution lines. Thereby, the admixture of recirculated air is divided into at least two stages, the system provides redundant failure tolerant operation, and the danger of ice formation in the air lines is reliably prevented even while the air conditioning units provide cold air at a temperature below the water freezing point.

High capacity air conditioning system with redundant staged recirculation air mixing for an aircraft

An aircraft air-conditioning system provides ventilation, air-conditioning and fire protection for a below-deck stairwell and cargo hold that may be equipped with passenger sleeping compartment containers. An air mixing unit mixes fresh air and recycled air to supply mixed air through a first supply air main line (,) and a supply air unit (,) into the freight hold (,), and through a second supply air main line (,) into the stairwell (,). A trimming air unit (,A) provides hot bleed air from the aircraft engines into the mixed air supplied through the first and second supply air main lines (,). An exhaust air line (,) extracts exhaust air from the freight hold (,), while an exhaust air supplemental line (,) extracts exhaust air from the stairwell (,), both of which are connected to an exhaust air main line with an exhaust air ventilator (,) that blows the exhaust air overboard. A bypass line (,) provides bypass air if needed for the demands of the ventilator (,). Regulating valves and non-return flap valves in the supply air line and in the exhaust air line regulate the flow of air and prevent back-flow. Temperature sensors are connected to a controller that regulates the temperature of the mixed supply air to achieve a comfortable temperature in the freight hold and in the stairwell. In the event of fire, the air valves are closed, to seal-off the freight hold (,) and prevent the spread of smoke into the stairwell or other ventilated areas.

Air-conditioning system for below-deck areas of a passenger aircraft

The below-deck space of an aircraft may be selectively configured as a freight hold or alternatively as a passenger sleeping cabin space by arranging a sleeping cabin container therein. An air conditioning system for this below-deck space provides air in a supply air main line (,), which branches off to at least one supply air delivery line (,). A first flange (,) is provided at the end of the supply air delivery line (,), and a seal collar (,) seals the end relative to the freight hold wall (,). When a sleeping cabin container is to be arranged in the below-deck space, a flap door (,) is pivoted into an open position, and the flange (,) at the end of a ventilation duct (,) of the sleeping cabin is connected directly to the flange (,). When the sleeping cabin container is removed from the freight hold, the flap door (,) is pivoted into a closed position, in which it covers the mouth opening of the flange (,), and allows an air flow into the freight hold only through the smaller restricted cross-section of an air throughflow opening (,) in the flap door (,). The air supply arrangement can be easily adjusted to meet the different air flow requirements of the sleeping cabin configuration and the freight hold configuration without requiring any recalibration of the air-conditioning system itself.

Reconfigurable air supply arrangement of an air-conditioning system for below-deck areas of a passenger aircraft

An air inlet provides air to an air consuming system of an aircraft, such as an auxiliary power unit, which consumes ram air during flight and which sucks in ambient outside air during ground operations of the aircraft. The inlet opening is flush with the outer surface of the fuselage skin. An air channel extends from the opening and is recessed into the fuselage. An air inlet lip bounds the downstream edge of the inlet opening. To prevent the formation of an airflow separation bubble in the air channel when air is sucked into the inlet during ground operations of the aircraft, an air guide element is arranged adjacent to the nose of the air inlet lip. In one embodiment the air guide element is an aerodynamically profiled auxiliary slat fixed in front of the nose of the air inlet lip to form an air guide gap therebetween. In another embodiment, the air guide element is a tiltable air guide flap that can be selectively deployed to extend downwardly from the nose of the air inlet lip during ground operation, and retracted flush into a recess of the air inlet lip during cruise flight of the aircraft.

Aircraft air inlet with airflow guide to prevent flow separation

An injector air outlet includes a temperature sensor and a smoke sensor to simultaneously carry out the functions of air recirculation and temperature and smoke monitoring within a closed interior space, such as a passenger cabin or a freight or cargo hold in an aircraft. The injector air outlet includes a housing wall (2) with an injector mixing chamber (3) therein. A primary supply air inlet (4) receives primary supply air (5) from the aircraft's air distribution duct network, and blows the primary supply air through an injection nozzle (7) into the mixing chamber (3) so as to create a reduced or negative pressure in the mixing chamber. Cabin exhaust air (10) is sucked through a secondary air inlet (9) and a secondary air channel (8) into the mixing chamber (3), due to the reduced pressure or suction effect therein. The primary air and secondary air are mixed together and then ejected forcefully back into the cabin or cargo hold. A sensor unit (12) including a temperature sensor (12A) and a smoke sensor (12B) is installed in the secondary air channel (8) so that a flow of exhaust air (10) is continuously positively caused to flow over the sensor unit (12).

Growing community of inventors

Bliedersdorf, Germany

Uwe Buchholz