Deutsches Zentrum Fuer Luft-und Raumfahrt E.v

Deutsches Zentrum Fur Luft-und Raumfahrt E.v.

Michael Oschwald

Wolfgang Armbruster

Justin Hardi

Dmitry Suslov

Yannik Miene

Jan Haubrich

Jörg Riccius

Katia Artzt

Lukas Opp

An injector device for an engine device for introducing a fluidic, in particular a liquid, fuel and a fluid, in particular liquid, oxidizing agent into a combustion chamber of the engine device is provided. The injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber. At least one first resonator element is associated with the at least one first injection element and/or at least one second resonator element is associated with the at least one second injection element.

Injector device for an engine device, engine device, and air- and/or spacecraft

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Heilbronn, Germany

Michael Oschwald