| Issue |
Volume 11, 2019
Progress in Propulsion Physics – Volume 11
|
|
|---|---|---|
| Page(s) | 591 - 612 | |
| DOI | https://doi.org/10.1051/eucass/201911591 | |
| Published online | 08 February 2019 | |
Design and tool anchoring for a 120-kilonewton expander cycle rocket engine liquid oxygen turbopump
Airbus DS GmbH Munich 81633, Germany
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 Authors, published by EDP Sciences, 2019
This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.