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Developing a roadmap for the post-processing of additively manufactured aerospike engines

 
: Buchholz, Maximilian; Gloder, Alessia; Gruber, Samira; Marquardt, Axel; Meier, Lucas; Müller, Michael; Propst, Martin; Riede, Mirko; Selbmann, Axel; Sieder-Katzmann, Jan; Tajma, Martin; Bach, Christian

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Fulltext ()

International Astronautical Federation -IAF-, Paris:
71st International Astronautical Congress, IAC 2020. Congress Proceedings. Online resouce : IAC CyberSpace Edition, 12-14 October 2020
Paris: IAF, 2020
https://dl.iafastro.directory/search/?q=event:IAC-2020
Paper 60613
International Astronautical Congress (IAC) <71, 2020, Online>
Bundesministerium für Bildung und Forschung BMBF (Deutschland)
03ZZ0232D; CFDµSAT
English
Conference Paper, Electronic Publication
Fraunhofer IWS ()
abrasive flow machining; laser powder bed fusion; chemical propulsion; aerospike engine; advanced nozzle design; additive manufacturing

Abstract
In this contribution, the results of a hot fire test campaign using a 500 N truncated annular aerospike engine are discussed as well as the underlying investigations. The designed aerospike serves as a proof of concept for the additive manufacturing of such an engine by the means of laser powder bed fusion (LPBF). Manufacturing, thermal treatment and mechanical post-processing was conducted by the Fraunhofer Institute for Material and Beam Technology (IWS). The aspired advantages of this manufacturing method opposed to conventional methods are a reduction of assembled parts leading to fewer machining interfaces and reduced costs associated with the assembly as well as the functional integration of complex internal cooling channel geometries into both the chamber wall and the central spike to ensure a better heat dissipation. Furthermore, the aerospike engine serves as a baseline for the later implementation of a secondary injection located on the surface of the divergent, supersonic nozzle part of the central spike to perform thrust vectoring. This fluidic thrust vector control is an important field of research at the Institute of Aerospace Engineering (ILR) of the Technische Universität Dresden. The hot fire tests using this bi-liquid propelled engine without thrust vector control (TVC) have been conducted at the ILRs own liquid oxygen and ethanol engine test bench. The results show a significant deviation from the designed thrust level of 500 N. Moreover, combustion instabilities have been observed and studied. These instabilities can mainly be traced back to the injector design and the corresponding high pressure losses at the inlets. As a result, a new project called CFDµSAT (funded by the German Federal Ministry for Education and Research) has been initiated, which is focused on the revision of the current engine design and particularly the injector element orifices with regard to additive manufacturing and finishing of the hydraulically relevant surfaces. To achieve better results during the post-processing of the printed parts, more advanced methods such as abrasive flow machining (AFM) or laser beam drilling will be utilized. The first short-term objective of the project is the examination of test specimens to identify decisive geometric parameters of additively manufactured injectors regarding optimized flow behavior. Subsequently, these findings will then be used for the design and manufacturing of a revised aerospike engine, whose performance will be investigated in a further test campaign.

: http://publica.fraunhofer.de/documents/N-633550.html