| The combustion products of aluminum ice solid rocket engine are hydrogen and Al2O3particles, and the mass fraction of condensed phase Al2O3particles is as high as95%forcomplete reaction, while load ratio may reach up to17, so the nozzle flow of aluminum icesolid rocket engine is considered as extra large load ratio gas-solid two phase flow. Nowadaysthe laws of gas-solid two phase flow in the condition of extra large load ratio are known littleyet, especially on the impact of the nozzle expansion, the thrust coefficient and specificimpulse of aluminum ice solid rocket engine. So it has important significance to research thelaws of gas-solid two phase flow of nozzle with extra large load ratio and explore the effectof particle phase parameters scale to nozzle design.In this paper Muscl-Hancock scheme and finite volume self-adaptive method are used tocalculate the gas-solid two phase flow filed, while gas phase interface flux is solved with HLLscheme and particle phase with Steger-Warming scheme. In this paper, the study focus onextra large load ratio two-phase flow parameters in nozzle and thrust performance with thedifferent load ratio, particle size and nozzle divergence angle, considering inviscid, laminarand k turbulent model. The numerical study shows that impulse loss of the extra largeload ratio gas-solid two phase flow is larger than that of pure gas phase. The differences of theresults for laminar flow and inviscid model are small, but inviscid model is a little higher, andthere are some differences between the results of inviscid model and turbulence model. In theextra large load ratio cases, the approximate isothermal thrust coefficient is the further awayfrom the integral thrust coefficient for the greater particle diameter. Approximate isothermalthrust coefficient would not be exact for the case of extra large load ratio.The results ofintegral thrust coefficient and isentropic thrust coefficient are fairly approach. |
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