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Numerical simulation of liquid rocket thrust chamber flows is a challenging task which requires a comprehensive tool validation strategy encompassing laboratory- to full-scale test cases. While the former are widely used as the first step to verify advanced numerical schemes and thermochemical models, the latter can often no more be simulated in a reasonable time frame due to the extreme computational effort necessitated by the enlarged dimensions and configurational changes. Conclusions drawn from tools with such limitations are only of little help for a thrust chamber designer and, hence, ill-posed to adequately tackle the simulation challenges of such a device. This paper discusses the modeling demands for numerical thrust chamber flow simulation tools and outlines the indispensable validation approach from laboratory- via subto full-scale configurations using consistent model features throughout the test cases. Consequences of this obligation are exposed to drive the tool setup. Exemplarily, the Airbus DS thrust chamber flow simulation philosophy is presented.

As part of a German nationally funded research programme “TARES,” a turbopump initiative has been started in recent years within Airbus DS GmbH. The aim of this study is to design a liquid oxygen (LOx) turbopump assembly (LOx-TPA) for a 120-kilonewton thrust class expander cycle rocket engine. To realize this objective, Airbus DS GmbH builds on in-house heritage, notably the turbopumps of the P111 and the H20 staged combustion engines. This experience serves as input for the design of the 120-kilonewton LOx turbopump. The current paper details the fluidic design of the turbopump, including the design philosophy and the anchoring on the heritage hardware. Discussed are the pump and turbine predesign starting from the configuration trade-off, the preliminary design, the flow path and blade design, and the design of inlet/outlet and the volute. Finally, the performance (nominal and off-design) is characterized by means of three-dimensional (3D) computational fluid dynamics (CFD) simulations.

The noise emission of rocket engine test facilities and their impact on the environment comes more and more into focus. The key drivers are the engine exhaust jet itself, and its interaction or even coupling with a subsequent guide tube. To increase understanding of the interaction, and in preparation of future test facility design, a cold gas subscale test campaign was conducted with a reference guide tube. It was found that the main influencing parameter is the distance between the nozzle exit and guide tube inlet. This article is published with the permission of the authors granted to 3AF - Association Aéronautique et Astronautique de France (www.3AF.fr) organizer of the Space Propulsion International Conference.