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Numerical study on the influence of gas-particle two-phase flow on the flow field in the throat region of an annular aerospike nozzle
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DOI：10.1016/j.jppr.2026.06.003.png)
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Abstract
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The gas-particle two-phase flow in solid annular aerospike nozzle rocket exerts a significant influence on the nozzle ablation and performance. However, the influence of nozzle contraction ratio on the two-phase flow characteristics in the throat region remains insufficiently explored. The analysis investigates the influence of the particle phase diameter, particle mass fraction, and nozzle contraction ratio on the flow field parameters of the nozzle throat region. For this purpose, numerical simulations employing the Euler-Lagrange method are conducted, and key performance indicators such as thrust efficiency, wall-adjacent temperature, and particle velocity are quantified. The results indicate that two-phase flow introduces performance loss; however, this loss can be mitigated to within 7% by selecting an appropriate nozzle contraction ratio (5.76 and 12.96). Additionally, the flow field parameters in the aerospike nozzle throat are influenced by the particle phase diameter, particle mass fraction, and nozzle contraction ratio. Among these factors, the temperature distribution is predominantly affected by the nozzle contraction ratio. Numerical results indicate that a nozzle with a contraction ratio of 12.96 can reduce the adiabatic wall-adjacent temperature from 2438 K to 1396 K. The velocity of the particle phase decreases as the diameter of the particle phase increases. These insights provide a reference for designing more efficient aerospike nozzles in solid rocket engines.
Keywords:
Solid rocket engine
Aerospike nozzle
Nozzle design
Two-phase flow
Numerical simulation
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