| Citation: | LING Wenhui, WEI Baoxi, HOU Jinli, et al. Numerical study on pure rocket mode performance characteristics of a RBCC engine[J]. Journal of Aerospace Power, 2025, 40（5）：20240433 doi: 10.13224/j.cnki.jasp.20240433
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To gain a comprehensive understanding of the performance characteristics and influencing factors of the pure rocket mode in rocket-based combined cycle (RBCC) engines, a full-axisymmetric characteristic RBCC engine benchmark flow path with a central rocket layout was designed and constructed. Additionally, a half-axisymmetric scarfed nozzle configuration RBCC engine and a continuously expanding nozzle configuration rocket engine flow path with the same designed expansion ratio were developed. Three-dimensional expansion flow field simulations were conducted under different thrust chamber pressures in the pure rocket mode, yielding the internal flow characteristics and thrust specific impulse performance characteristics under various nozzle configurations, secondary flows, and rocket propellant schemes. The results indicated that in the pure rocket mode, the non-ideal continuous expansion flow state led to a loss of specific impulse performance, with the specific impulse efficiency being below 80%. The strong shock wave after the large sudden expansion led to a total pressure loss, which was the main mechanism for performance degradation. The overall axisymmetric nozzle configuration had a specific impulse efficiency decrease of about 8% compared with the continuous expansion nozzle. The semi-axisymmetric scarfed nozzle can reduce the total pressure loss of the expansion and improve the specific impulse efficiency. Introducing a secondary flow can adjust the expansion-compression wave system structure to a certain extent to reduce the total pressure loss. Increasing the total temperature of the secondary flow can be beneficial to enhancing overall performance.
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