Hong Yeong PARK, Yun Hyeong KANG, Chang Han BAE, Jeong Soo KIM

DOI Number: 10.60853/cryq-dv86

Conference number: HiSST-2024-00341

A numerical simulation was conducted to scrutinize an unsteady physics which shows a stepwise increase of thrust performance in the later part of the combustion under the fuel-rich conditions. The nozzle outflow region was included in the calculation domain to reflect the influence of the atmospheric pressure condition. The flow field was analyzed using the RANS (Reynolds-Averaged Navier-Stokes) equation, and a non-adiabatic diffusion flamelet with 21 species and 84 reactions was applied to simulate the flame structure. As a result, the pressure and thrust calculated by the simulations were in good agreement with the experimental ones. However, an abrupt increase of thrust performance
observed at the later stage of the combustion duration was not clearly captured in the transient results. This indicates a limitation of the combustion model employed in calculating the abnormal phenomenon of thrust change.

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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