Modeling of H2/O2 single-element rocket thrust chamber combustion at sub- and supercritical pressures with different computational fluid dynamics tools

H Riedmann,O Knab,B Ivancic,D Banuti,K Hannemann

doi:10.1051/eucass/201911247

Abstract

This paper derives from the cooperation between DLR and Airbus DS within the work package “CFD Modeling of Combustion Chamber Processes” conducted in the frame of the Propulsion 2020 project. In a joint strategy, DLR Göttingen and Airbus DS Ottobrunn have identified a number of test cases with gradually growing complexity where adequate test data are available for proper successive validation of the computational fluid dynamics (CFD) tools to be used in an industrial environment. This work highlights the simulation results for the Mascotte A-10 and A-60 test cases as presented at the 2nd International Workshop on Rocket Combustion Modeling in Lampoldshausen 2001 by ONERA and SNECMA [1]. These two test cases are characterized by different chamber pressures (10 and 60 bar) and, consequently, by oxygen injection conditions which are subcritical in one case and transcritical in the other case. The test cases are treated with three different CFD codes: the DLR TAU Code (only A-60 case), the Airbus DS in-house tool Rocflam3, and the commercial CFD tool ANSYS CFX incorporating several modeling extensions by Airbus DS. To the knowledge of the authors, this paper is the first one which covers both the A-10 and the A-60 test cases.

Highlights

The main target of the cooperation between DLR and Airbus DS within Propulsion 2020 is extending knowledge and competence in the area of rocket propulsion© The Authors, published by EDP Sciences
Several studies have been conducted with Roc§am3 using the Lagrangian module for the injection of the transcritical oxygen in the A-60 test case, but while they all showed good convergence behavior and plausible results, the agreement with the characteristic §ame shape known from the experimental data was not satisfactory
This paper provides a comparison between the three dierent codes: Roc§am3, CFX, and TAU, being applied to the Mascotte A-10 and A-60 test cases, which operate in the sub- and supercritical pressure regimes of cryogenic coaxial injection

Summary

Introduction

The main target of the cooperation between DLR and Airbus DS within Propulsion 2020 is extending knowledge and competence in the area of rocket propulsion© The Authors, published by EDP Sciences. Several studies have been conducted with Roc§am3 using the Lagrangian module for the injection of the transcritical oxygen in the A-60 test case, but while they all showed good convergence behavior and plausible results, the agreement with the characteristic §ame shape known from the experimental data (see Fig. 3) was not satisfactory.

Results

Conclusion