Airbus Operations Gmbh

Airbus Operations (s.a.s.)

Airbus Operations Sl

Jan Barkowsky

Etienne Foch

Jean-Louis Lando

Jan Dittmar

Xavier Roboam

Paul-Emile Roux

Javier Fraile Martin

Jérôme Mavier

Laurent Duffau

Thierry Garcia

Charles Renard

Antón Méndez Díaz

Neus Busquets More

Christoph Mevenkamp

Antón MÉNDEZ DÍAZ

A method for controlling takeoffs of mechanical energy and/or air on a turbine engine for the propulsion of an aircraft. It is based on a protocol for the exchange of a request/authorization between and by the energy manager and a system for controlling the turbine engine. This protocol is implemented as a result of a modification of the takeoff requirement. It is intended to check whether the surge margin is compatible with the modification of the takeoff requirement and, if the need arises, to apply temporary measures in order to prevent surge in the turbine engine, for example by providing at least a part of the energy requirements by a buffer. This permits the optimization of the operation of a turbine engine for the propulsion of an aircraft, while avoiding the risk of surge of the turbine engine.

Method and device for testing samples on a turbine engine minimizing the risk of surge by the exchange of information between an energy manager and a system for testing the turbine engine

An engine bleed air system of an aircraft, comprising a heat exchanger which comprises a rectangular core with a rectangular outlet section, a cylindrical outlet duct and a transition area between the rectangular outlet section of the rectangular core and the cylindrical outlet duct, and at least a downstream system, further comprising a flow deflector located at least in the cylindrical outlet duct, such that the outlet flow characteristics homogeneity are improved and a particular flow deflection and distribution of the outlet flow is achieved, avoiding the damage of the at least one downstream system. The invention also provides a method for homogenizing the temperature of the outlet flow of a heat exchanger outlet in an engine bleed air system of an aircraft.

Heat exchanger outlet deflector

The invention relates to an air supply system of an aircraft, in particular of a passenger aircraft, which comprises a fresh air system, through which fresh air can be supplied to an aircraft cabin, a circulating air system, which is coupled to the fresh air system and through which used cabin air can be supplied to the fresh air system, a cooling air system for cooling an air conditioning system of the aircraft disposed in the fresh air system, and a ventilation system coupled to the cooling air system for ventilating an installation space of the air conditioning system. The air supply system includes a device for fluidically coupling the cooling air system and the ventilation system. The device is disposed and configured inside the fuselage of the aircraft such that the air in one system can be driven through the air flow in the other system. The invention also relates to a method for mixing two air streams in an air supply system of this kind of an aircraft.

Air supply system of an aircraft and method for mixing two air streams in an air supply system

The invention concerns an aircraft comprising a reversible rotary electrical machine), a wheel () for imparting movement to a stream of air, linked to said machine (), a first ventilation duct () configured to supply said wheel () with air, an electricity distribution network (), a reversible power converter () connected to said machine () and to said network (), and a control circuit () configured to control said converter () for, in a motor operating mode of said machine (), taking a supply current from said network () to supply said machine () and drive said wheel (), and, in an alternator operating mode of said machine (), in which a stream of air flows in said first ventilation duct () and imparts movement to said wheel (), to provide supply power to said network () which is generated by said machine () driven by said wheel ().

Aircraft comprising a reversible rotary electrical machine

An air conditioning system in an aircraft is provided. The system comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air line is connectable to a starter turbine for a main engine. With the use of air from a compressor of an air conditioning pack it is not necessary to switch off the air conditioning pack; bleed air removal from the auxiliary power units becomes obsolete; and, since there is no unnecessary discharge of compressed air from a bleed air system, noise pollution on the ground is reduced.

Main engine start by means of an aircraft air conditioning system

Growing community of inventors

Schwerin, Germany

Jan Barkowsky