The simulation of cryogenic flows in rocket combustion chambers is challenging because we have to consider a reactive mixture over a wide temperature and density range. This necessitates the use of more advanced fluid models that impose additional computation overhead. In this study we compare two equation of state (EOS) mixture approximation approaches for cryogenic flows in rocket combustion chambers and present a computationally efficient implementation within a Reynolds Averaged Navier Stokes (RANS) context. The numerical study is validated with experimental results of a lab-scale rocket combustion chamber with optical access.
Efficient Handling of Cryogenic Equation of State for the Simulation of Rocket Combustion Chambers
Lect.Notes Mechanical Engineering
International Seminar on Non-Ideal Compressible-Fluid Dynamics for Propulsion & Power ; 2018 ; Bochum, Germany October 04, 2018 - October 05, 2018
2020-07-09
12 pages
Article/Chapter (Book)
Electronic Resource
English
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