Justin Steven Hardi

High-frequency combustion instability mechanism of a liquid oxygen/methane swirl coaxial injector in an optically accessible chamber

Alexander Bee, Michael Börner, Jan Martin, Wolfgang Armbruster et autres

Injector elements are an elemental sub-component of any liquid rocket engine, as they are critical in influencing engine efficiency and combustion stability. Therefore, characterizing such elements is of great importance. In regeneratively cooled rocket engines, significant changes in fuel injection temperature can …

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Modelling thermoacoustic stability of cryogenic rocket engines with novel acoustic network model elements

Nicolás de Jong Cantariño, Wolfgang Armbruster, Justin Steven Hardi, Michael Börner et autres

Reliable and computationally efficient prediction capabilities for combustion instabilities in liquid propellant rocket combustion chambers are still rare. This study uses a low-order tool based on the well-known acoustic network model principle to map the stability limits of two different research rocket …

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Towards Determining OH*, CH* and C2* Concentrations in LOX/Methane Rocket Engine Tests via Emission Spectroscopy as a Potential Means to Assess Climate Impact

Leon Lober, B. Knapp, Justin Steven Hardi

With the number of rocket launches increasing almost exponentially in the last years, a trend that will presumably continue, the question of the environmental impact of rocket launches becomes more and more important. However, rocket plume investigations in the past were mostly …

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Reseearch and technology activities at the DLR Institute of Space Propulsion

Justin Steven Hardi

Visualization of the Detonation Wave Structure in a Small-Scale Hydrogen–Oxygen Rotating Detonation Combustor

Wolfgang Armbruster, Ewen Bard, Michael Börner, Kilian Rheindorf et autres

This study presents the high-speed visualization of the detonation wave structure in a small-scale hydrogen–oxygen rotating detonation combustor. A 68 mm Rotating Detonation Combustor was modified with a quartz-glass ring, such that radial optical access into the annular detonation chamber was realized. …

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IDDES of a LOX/CH4 Model Rocket Combustion Chamber at Real Gas Conditions

Timo Seitz, Ansgar Lechtenberg, Jan Martin, Justin Steven Hardi et autres

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Multiphysics Simulation and Benchmarking of Laser-Induced Ignition under Propellant Flashing Conditions of an Experimental Rocket Combustion Chamber

Christian Sessler, Jan Wilhelm Gärtner, Andreas Kronenburg, Alexander Bee et autres

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Characterization of a LOX/natural gas liquid-centered swirl coaxial injector element in an optically accessible combustion chamber

Alexander Bee, Michael Börner, Jan Martin, Wolfgang Armbruster et autres

Despite the fact that swirl coaxial injector elements are a popular choice in the design of LOX/methane liquid rocket engines, there is still a distinct lack of experimental studies optically evaluating their behavior under hot-fire conditions. Such optical data is essential for …

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Influence of Injector and Chamber Design on LOX/CH4 Combustion Instabilities

Jan Martin, Wolfgang Armbruster, Michael Börner, Justin Steven Hardi et autres

A shear-coaxial element is a prominent choice in terms of injection technology for bipropellants with a high density ratio. While this type of injector performed well for liquid-oxygen and hydrogen combustion in an optically accessible single-element combustor and a multi-injector thrust chamber, …

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Numerically Efficient Non-Adiabatic Real Fluid Flamelet-Based Combustion Modeling Approach for Liquid Rocket Engine Thrust Chambers

Marvin Pommerening, Daniel Eiringhaus, Jan Martin, Bernhard Knapp et autres

In the present work, a consistent thermophysical modeling framework for the representation of real fluid effects via a single-phase dense gas approach is discussed and its prediction quality at transcritical conditions typical for liquid-propellant rocket engine injection is investigated. It is linked …

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Design and testing of a hydrogen–oxygen pre-detonator for rotating detonation engines

Wolfgang Armbruster, Ewen Bard, Stéphane Boulal, Michael Börner et autres

Abstract Rotating Detonation Engines (RDEs) have the potential to significantly increase the performance of liquid-propellant rocket engines. Besides, they are also a promising improvement for gas turbine combustors. Therefore, there is a rapidly growing interest world-wide into this technology. One critical aspect …

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Designing a mission concept for atmospheric plume measurements during a rocket launch event

Andreas Marsing, Christiane Voigt, Anke Roiger, Matthias Nützel et autres

The frequency of space launches has increased dramatically as costs plummet and demand rises with the advent of use cases (such as mega constellations or larger-scale exploration). This increase in launch cadence is enabled by reusable launchers, whose technology is progressing in …

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