Airbus Defence and Space Gmbh

Airbus Operations Gmbh

Airbus (sas)

Mtu Aero Engines Gmbh

Eads Deutschland Gmbh

Mtu Aero Engines Ag

Airbus Corporation

Spawnt Private S.a.r.l.

Dorner

Eads France Sas

Jürgen Steinwandel

Erwin Bayer

Claus Hoffjann

Albin Platz

Christian Bauch

Emmanuel Joubert

Rumen Deltschew

Sven Holl

Christian Karch

Martin Bussmann

Gerd Lippold

Blanka Lenczowski

Paulin Fideu

Javad Mohsseni

Michael Hofmann

Jorge Alejandro Carretero Benignos

Helmut Piringer

Christian Wolff

Alexander Kaiser

Domenico Furfari

Thomas Kränzler

Michael Judas

Jan Van Toor

Werner Zimmermann

Bernard Duprieu

Heiko Fietzek

Roland Lang

Johannes Stuhlberger

Wilhelm Wulbrand

Nikolaus Ohrloff

Stefan Laure

Alexander Ohnesorge

Michael Pilawa

Didier Simonet

Dietrich P Jonke

Christian Wilhelmi

Stefan Stückl

Franziska Uhlmann

Eggert Reese

Harald Geiger

Jochen Laun

Philipp Thümmler

Claudio Dalle Donne

Ante Kurtovic

Martin Englhart

Ning Wang

Florian Stagliano

Ulrike Heckenberger

Werner Scholz

Agata Godula-Jopek

Martin Ströer

Walter Rothammel

Lucien Prisse

Ludovic Ybanez

Marko Gollasch

Kan-Ern Liew

Ernst Sigmund

Blanka Lencszowski

Rudolf Voit-Nitschmann

Theo Hack

Rolet Sebastien

John Price

A cooling device for use in alternating magnetic fields include an evaporator part defining a first volume for evaporating a cooling medium contained therein, the evaporator part being made of an electrically and magnetically non-conductive material, and a condenser part defining a second volume for condensing the cooling medium contained therein, the condenser part being in fluid connection with the first volume.

Cooling device for use in alternating magnetic fields, coil arrangement, electric machine, and aircraft

A battery comprising a fluid electrolyte, a casing configured to contain the electrolyte, an anode placed in contact with the electrolyte in the casing, and a cathode placed in contact with the electrolyte in the casing. The battery comprises a temperature control device configured to modify the temperature of the electrolyte, a circulating device configured to circulate the electrolyte in the casing and between the casing and the temperature control device. Also, a method for regulating the temperature of a battery in which a fluid electrolyte is circulated in a battery casing comprising an anode and a cathode, and through a temperature control device configured to modify the temperature of the electrolyte.

Battery with temperature control device and method for regulating the temperature of a battery

An aircraft drive device () for creating propulsion and/or lift of an aircraft, the drive device comprising a rotating shaft (), a rotating shaft bearing (), a rotating shaft drive machine () for rotationally driving the rotating shaft (), and a housing (), wherein the rotating shaft bearing () and the rotating shaft drive device () are arranged in an interior of the housing () and the rotating shaft () protrudes to the outside of the housing () through a housing opening () of the housing (), wherein in the region of the housing opening () an overvoltage arrester device () is arranged which is designed for diverting an overvoltage present at the rotating shaft ().

Aircraft drive device and aircraft provided with a drive device

A structure for high temperature applications includes a base structure which includes a ceramic composite material, and a coating of a metal-semimetal compound, a metal boride, a metal carbide and/or a metal nitride. Furthermore, a production method and a coating device produces structures which resist high temperature applications with higher process temperatures and difficult chemical conditions.

Structure or structural member for high temperature applications and method and apparatus for producing thereof

A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

Hybrid electric drive train for VTOL drones

A structure for high temperature applications comprises a base structure which includes a ceramic composite material, and a coating of a metal-semimetal compound, a metal boride, a metal carbide and/or a metal nitride. Furthermore, a production method and a coating device produces structures which resist high temperature applications with higher process temperatures and difficult chemical conditions.

Structure or component for high temperature applications, as well as methods and apparatus for producing same

The embodiments relate to a switch device for an electrochemical energy store having: a film transistor device that comprises at least one organic transistor, can be mounted in a planar manner on at least one electrode of the electrochemical energy store, can be controlled by an external voltage source, and is designed in the form of a controllable electrical resistor that is connected, in series, to an internal resistor of said electrochemical energy store.

Switching device for an electrochemical energy store and energy storage system

A drive unit includes a combustion chamber for combusting a fuel/air mixture, and a fuel cell device, wherein the fuel cell device includes at least one fuel cell, which in each case includes an anode that is couplable to a fuel line, a cathode that is couplable to an air source, and a fluid outlet and is arranged upstream of the combustion chamber. The combustion chamber further includes a combustion chamber inlet for supplying the fuel/air mixture, and a combustion chamber outlet for discharging exhaust gas, and the combustion chamber inlet is connected to the fluid outlet of the fuel cell device. In this way a hybrid drive unit can be provided which apart from mechanical power also generates electrical power at high efficiency.

Drive unit, method for providing power, and use of a drive unit

A method for manufacturing a solid oxide fuel cell element by layer-wise buildup wherein at least one section of the element is built up by carrying out a step that at least includes the following at least once: applying a layer section of a particulate ceramic material with predefined dimensions onto a base layer in a predefined area and heating the layer section by means of a heat source such that the particles of the ceramic material connect to one another within the predefined dimensions. The solid oxide fuel cell element manufactured with the method is realized in one piece, as well as highly compact, and has a low weight.

Method for manufacturing a solid oxide fuel cell element by layer-wise buildup and solid oxide fuel cell element

A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850&#xb0; C. to 1100&#xb0; C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device.

Exhaust gas treatment of gas turbine engines

The invention relates to a method for plasma reformation of fuel, in particular kerosene, which method comprises the steps of: feeding fuel through a line to the inlet of an expansion nozzle; supplying energy from an energy source by way of a hollow waveguide to generate a plasma state in the expansion nozzle; injecting further fuel through nozzles into the arising plasma flame in order to decompose the fuel in the heat into components such as CO, C and H; and expanding the plasma flame at high speed into the combustion chamber.

Method and device for plasma reformation of fuel for engine applications

A sonotrode for accelerating shot for ultrasonic shot peening, includes at least one vibration exciter and a cover element that has an output side of the sonotrode, wherein the cover element is to be operated by means of the vibration exciter with a forced vibration such that the value of the vibration amplitude of the cover element corresponds essentially to the value of the vibration amplitude of the vibration exciter, where from this cover element another cover element is set out on the further side of the vibration exciter and in which between these two cover elements is stretched a majority of spring elements in the form of tension springs.

Sonotrode especially for accelerating shot for ultrasonic shot peening

Growing community of inventors

Uhldingen-Mühlhofen, Germany

Jürgen Steinwandel