Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Appearance of impact starting of the flow in exhaust diffuser used for altitude rocket engine tests

Published: 14.01.2019

Authors: Zakharov V.S., Gouskov O.V., Berezhnoy V.N.

Published in issue: #1(85)/2019

DOI: 10.18698/2308-6033-2019-1-1841

Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts

We considered the influence of pressure increasing velocity in combustion chamber of rocket engine on forming and structuring of the flow in exhaust diffuser with round section. This exhaust diffuser is used for imitation of altitude conditions when performing the bench tests. Given phenomenon is typical for nozzles of rocket engines of carrier rocket third stages, upper-stage rockets and orbital transfer vehicles, which have a great divergence ratio (100…500) and big profile curvature in axial direction. Examples of such engines are “Vinci” engine for carrier rocket Ariane 6, RD0146D engine and others, developed at the moment. Investigations are based on flow numerical simulation for compressed viscous gas with variable heat-transfer properties. Spalart—Allmaras one-parameter model is used as turbulence model. AUSM+ scheme is used for calculation of the flows at the borders of computational grid meshes. Thermodynamic properties of working medium are calculated on the base of equilibrium model of chemical reacted mixture of hydrogen and oxygen. We demonstrated the principal difference between flow structure in the nozzle and the duct of exhaust diffuser at abrupt and smooth pressure  increase in combustor of rocket engines

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