Airbus Operations Gmbh

B/e Aerospace, Inc.

Airbus (sas)

Torsten Trümper

William J Godecker

Matthias Reiss

Jens Schult

Qiao Lu

Holger Bammann

Ahmet Kayihan Kiryaman

Didier Poirier

Martin Sieme

Ekkehard Lohse

Paul Chen

Christian Schaarschmidt

Jana Caspari

Christopher Warsch

A system for providing a pressurized liquid, having a reservoir for the liquid, which has a discharge and a feed, having a pump, having a first valve, having a separate filter chamber, having an inlet and at least one outlet, and a compressible, closed buffer body. The pump is between the discharge of the reservoir and the filter chamber and configured to increase pressure of the liquid within the filter chamber, the first valve between the feed of the reservoir and the filter chamber and configured to open in the direction of the reservoir upon attainment or exceedance of a minimum pressure of the liquid in the filter chamber. The buffer body is in the filter chamber such that it can be surrounded by liquid.

System for providing a pressurized liquid

An expansion tank system for a liquid cooling system includes a first chamber for receiving a coolant, a second chamber for pressurized gas, a first gas conveying device for conveying gas from the first to the second chamber, a second gas conveying device for conveying gas from the second to the first chamber, a first pressure sensor in fluid communication with the first chamber, and a control unit connected to the first gas conveying device, the second gas conveying device and the first pressure sensor for controlling the second conveying device to selectively convey gas from the second to the first chamber if a pressure measured through the first pressure sensor is below a predefined first threshold value, and for controlling the first conveying device to convey gas from the first to the second chamber if a pressure measured through the first pressure sensor is above a second threshold value.

Expansion tank system

A temperature regulating system for at least one galley compartment for an in-flight kitchen which is intended for installing in a transport apparatus or vehicle, especially in an aircraft, includes a controllable cooling and heating element, which is designed for selectively cooling or heating a specified section of the cooling and heating element, and a heat-insulating partitioning wall, which at least partially adjoins an encompassing side edge of the cooling and heating element and encloses the specified section of the cooling and heating element. The heat-insulating partitioning wall is designed for separating an interior space of the galley compartment from an interior of a section of a fluid duct which extends in the in-flight kitchen.

Temperature regulating system for a galley compartment of an in-flight kitchen

A supply system with a plurality of consumers, which can be supplied with a minimum volumetric flow by the supply system to ensure their operational function, wherein the supply system exhibits a network of lines with a plurality of lines, which are each hooked up to the consumers, and a pump connected to the lines for generating a volumetric flow of supply fluid in the lines, wherein the supply system incorporates a network of lines in which consumers are fluidically connected in parallel in relation to the pump arrangement, and wherein each consumer has allocated to it at least one flow control valve functionally placed upstream from the respective consumer in the cooling circulation as viewed from the position of the pump in the direction of flow.

Supply system with a plurality of consumers

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 chiller for an aircraft galley that is sized to be disposed in a compartment for housing beverage carts, the chiller comprising a vapor cycle refrigeration system with a liquid cooled condenser located within the housing and a liquid cooling unit located within the housing. Further, the vapor cycle refrigeration system and the liquid cooling unit have a combined footprint that is less than a footprint of a food and beverage cart within the housing, such that the space occupied by the chiller displaces no more than one beverage cart.

Aircraft galley air chiller system

A cooling unit in a transport unit includes power electronics; a heat exchanger for thermally coupling a cooling agent of a central cooling system of the transport unit with air of the cooling unit to cool one or more generating devices; and a heat pipe for heat dissipation of the power electronics. At a first portion of the heat pipe, at least some of a working agent is in the liquid phase and, at a second portion of the heat pipe, at least some of the working agent is in the gas phase. In the first portion of the heat pipe, heat from the power electronics is absorbed by evaporating the working agent in the liquid phase. In the second portion of the heat pipe, heat is released to the cooling agent by condensing the working agent in the gas phase.

Growing community of inventors

Hamburg, Germany

Torsten Trümper