Airbus Operations Gmbh

Airbus Deutschland Gmbh

Ahmet Kayihan Kiryaman

Andreas Frey

Ozan Uluc

Markus Piesker

Carsten Colberg

Markus Kerber

Martin Sieme

Michael Dreyhaupt

Peter Schwebke

Thomas Scherer

Dariusz Krakowski

Sebastian Roering

Torsten Trümper

Jürgen Kelnhofer

Matthias Witschke

Johannes Chodura

In a method for operating an aircraft cooling system a cooling medium is guided through a cooling circuit, which is connected to a refrigerating machine and to at least one cooling station associated with a cooling energy consumer, to supply cooling medium cooled by the refrigerating to the cooling station. A temperature of the cooling medium upstream of the cooling station and a temperature of the cooling medium downstream of the cooling station are detected. The mass flow of cooling medium supplied to the cooling station is controlled in dependence on a thermal output of the cooling energy consumer and in dependence on a difference between the temperature of the cooling medium upstream of the cooling station and the temperature of the cooling medium downstream of the cooling station.

Method for operating an aircraft cooling system and aircraft cooling system

A cooling system, in particular for use on board an aircraft, includes a cooling circuit allowing circulation of a two-phase refrigerant therethrough, an evaporator disposed in the cooling circuit, and a condenser disposed in the cooling circuit. A plurality of subcoolers is arranged in series in the cooling circuit downstream of the condenser.

Cooling system with a plurality of subcoolers

An accumulator arrangement for use in a cooling system suitable for operation with two-phase refrigerant includes a condenser having a refrigerant inlet and a refrigerant outlet. The accumulator arrangement further includes an accumulator for receiving the two-phase refrigerant therein, the accumulator having a refrigerant inlet connected to the refrigerant outlet of the condenser and a refrigerant outlet. Finally, the accumulator arrangement includes a subcooler having a refrigerant inlet and a refrigerant outlet, the refrigerant inlet of the subcooler being connected to the refrigerant outlet of the accumulators, and the subcooler being arranged at least partially within the interior of the accumulator.

Accumulator arrangement with an integrated subcooler

The invention discloses the multistage cooling of an aircraft electronic system () with at least one electronic component which delivers heat. The multistage feature results from the use of a plurality of circuits for transferring the waste heat. An internal coolant () circulating in a closed circuit which is thermally coupled to the electronic component carries heat from the at least one electronic component to a heat exchanger () which delivers the heat to an external coolant which flows and/or circulates from a source outside of the aircraft electronic system () through the heat exchanger () to a sink outside of the aircraft electronic system (). The internal coolant flows from the heat exchanger () in the direction of the at least one electronic component and/or circulates in a closed circuit.

Multistage cooling of electronic components of an aircraft

A cooling system for cooling food on board an aircraft includes a cooling circuit adapted to supply cooling energy to at least one cooling station, a refrigerant circulating in the cooling circuit selected such that it is convertible at least partially from the liquid to the gaseous state of aggregation on releasing its cooling energy to the at least one cooling station and subsequently convertible back at least partially to the liquid state of aggregation again by an appropriate pressure and temperature control in the cooling circuit, and a refrigerant container including a receiving space arranged in an interior space of the refrigerant container which receives the refrigerant circulating in the cooling circuit, the receiving space of the refrigerant container connected to the cooling circuit by a flow line for discharging the refrigerant from the receiving space and by a return line for returning the refrigerant into the receiving space.

Cooling system and method for operating a cooling system

The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system, the aircraft electronics cooling system providing a thermal coupling between an electronic device to be cooled and the liquid cooling system of the aircraft. A coolant delivered by the liquid cooling system may flow through a board of the electronic device, through a heat sink on which the electronic device is arranged and/or through a housing in which the electronic device is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Aircraft electronics cooling apparatus for an aircraft having a liquid cooling system

A system for air conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer in order to supply the central mixer with air at a desired low temperature. A first recirculation system is designed to remove exhaust air from a first aircraft cabin region and is connected to the central mixer in order to lead the exhaust air into the central mixer. A second recirculation system is designed to remove exhaust air from a second aircraft cabin region and is connected to first and second local mixers in order to lead the exhaust air into the local mixers, the local mixers also receiving mixed air flow from the central mixer. The second recirculation system includes a cooling unit which is designed to cool the recirculation air removed from the second aircraft cabin region before delivery to the first and second local mixers.

System and method for air conditioning an aircraft cabin with improved cooling capacity

A cooling system () for cooling an aircraft device () comprises an evaporator () for receiving a fluid (F) which is to be evaporated, a first adsorber () which contains a medium () for the adsorption of the fluid (F) which is evaporated in the evaporator (), as well as a second adsorber () which contains a medium for the adsorption of the fluid (F) which is evaporated in the evaporator (). A control system () is adapted to establish or to interrupt a fluid connection between the evaporator () and the first and/or the second adsorber(s) ().

Cooling system and method for cooling an aircraft device

The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system (), the aircraft electronics cooling system providing a thermal coupling between an electronic device () to be cooled and the liquid cooling system () of the aircraft. A coolant delivered by the liquid cooling system () may flow through a board of the electronic device (), through a heat sink on which the electronic device () is arranged and/or through a housing in which the electronic device () is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

In a cooling system () for cooling heat-generating installations () in an aircraft, with a refrigerating installation (), at least one refrigeration consumer () and a refrigeration transport system () connecting the refrigerating installation () and the refrigeration consumer (), it is provided that the refrigerating installation () comprises at least one refrigeration machine () which covers the maximum refrigeration requirement of the at least one refrigeration consumer () and in that the at least one refrigeration consumer () is supplied with cold generated in the refrigerating installation () via a refrigerating agent circulating in the refrigeration transport system ().

Cooling system for cooling heat-generating installations and for maintaining the temperature of closed-off areas at below cabin temperature in an aircraft

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Hamburg, Germany

Ahmet Kayihan Kiryaman