A four-engine liquid launch vehicle is studied to analyze the influence of afterburning reactions on the plume flowfield of a rocket exhausted jet. To accurately simulate the afterburning flow of the rocket exhaust plume with multispecies and chemical reaction, the three-dimensional compressible Navier–Stokes equations and realizable turbulence model are used to establish the rocket supersonic plumes impact model. Finite-rate chemical kinetics was used to simulate the chemical reactions. The validity and accuracy of the afterburning reaction flow model are verified by comparing them with the corresponding experiment data and previous calculations in the literature. On this basis, the chemical reaction and frozen flow of the four-engine liquid rockets in the launching process are simulated. The results show that afterburning mainly occurs in the gas accumulation region and the mixture region of air and gas. Compared with the frozen flow, the mole concentrations of hydrogen and carbon monoxide in exhaust gas decreased, and those of the water vapor and carbon dioxide increased in the reaction flow. The temperature and pressure of the deflector surface are, respectively, 24.9 and 7.2% higher than those in the frozen flow. The numerical results with afterburning reaction are closer to the real rocket gas. This study demonstrates that our model can effectively simulate the afterburning flowfield, and it can be useful for the design of liquid rocket platforms.
Numerical Studies of Afterburning on Impingement Flowfield of the Four-Engine Rockets
Journal of Spacecraft and Rockets ; 57 , 6 ; 1284-1294
2020-05-27
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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