The CryoROC (Cryogenic ROcket Combustion) software, a sophisticated multi-phase Navier-Stokes code developed by Astrium (former DaimlerChrysler Aerospace AG -Dasa) is used to analyse complex flows in combustion chambers and nozzles of cryogenic hydrogen/oxygen rocket engines. This paper presents an introduction and overview of CryoROC's modelling philosophy and to discusses typical applications demonstrating the potential of the code to support the layout and optimisation process of advanced rocket engines. Section 1 gives an introduction of industrial needs and environment while section 2 describes the code's main features. The importance of CryoROC's essential part, the Lagrangian droplet tracking module, for accurate wall heat flux predictions, is outlined in Section 3. In Section 4, a single injector element test case is recomputed by CryoROC. With the results obtained, the necessity of a detailed injector near-field resolution to predict global engine characteristics is discussed. Finally, in section 5, a special application of the CryoROC code is presented, i.e. a transpiration-cooled subscale chamber is computed and compared to available test data.
展开▼
