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首页> 外文期刊>International Journal of Heat and Fluid Flow >Numerical study of choked cavitation in high temperature hydrocarbon liquid jets
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Numerical study of choked cavitation in high temperature hydrocarbon liquid jets

机译：高温烃类液体射流中气蚀现象的数值研究

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A numerical study was conducted on a practical plain orifice injector issuing pressurized high-temperature aviation fuel, in order to simulate injection of fuel after use as a coolant in the active cooling system of a hypersonic vehicle. A three-dimensional unstructured mesh inside the orifice was created using ICEMCFD (TM) S/W, and the CFD analysis was performed using FLUENT (TM) S/W. A multiphase mixture model was used to simulate cavitating two-phase flow, and the full cavitation model was activated to predict the mechanism and effects of cavitation induced by the high fuel vapor pressures at elevated temperature conditions. The simulation was performed for fuel heated up to 553 K (280 degrees C) at an upstream pressure (P-inj) of up to 1.0 MPa, and various ambient pressures (P-infinity). The results were compared with experimental data, and the simulation was found to predict the discharge coefficient (C-d) with respect to the fuel injection temperature (T-inj) quite well at the given conditions. The CFD analyses for high fuel temperature conditions revealed that the mainstream flow inside the injector separates from the orifice wall at the vena contracta due to the generated fuel vapor cavity, and the attached flow at the end of the cavity separates again to produce a very small recirculation zone. In addition, for a given pressure drop, the sharply decreasing trend of the mass flow rate (or C-d) with increasing T-inj varies depending on P-infinity, because the mass flow choking is determined by the relationship between P-infinity and the vapor pressure (P-sat) at T-inj. Finally, C-d with respect to cavitation number was found to follow an almost identical line, even at different P-infinity. This confirms that choked cavitation at high fuel temperature conditions depends on the downstream pressure of the orifice, and the effect of cavitation on C-d at high T-inj is well represented by the cavitation numbers, regardless of P-inj, P-infinity, and T-inj.
机译：为了模拟在超音速飞行器的主动冷却系统中用作冷却剂后的燃料喷射情况，对实用的普通孔口喷射器进行了数值研究，该喷射器喷射了加压的高温航空燃料。使用ICEMCFD（TM）S / W创建孔内的三维非结构化网格，并使用FLUENT（TM）S / W进行CFD分析。使用多相混合物模型来模拟空化两相流，并激活完整的空化模型，以预测高温条件下高燃料蒸气压引起的空化的机理和影响。针对在高达1.0 MPa的上游压力（P-inj）和各种环境压力（P-infinity）下加热至553 K（280摄氏度）的燃料进行了模拟。将结果与实验数据进行比较，发现在给定条件下，仿真可以很好地预测相对于燃料喷射温度（T-inj）的排放系数（C-d）。 CFD对高燃料温度条件的分析表明，由于产生的燃料蒸气腔，喷油器内部的主流与腔孔处的孔壁分离，而腔末端的附着流再次分离，从而产生非常小的回流区。另外，对于给定的压降，质量流量（或Cd）随T-inj的增加而急剧下降的趋势随P-无穷大而变化，因为质量流阻塞由P-无穷大与P-无穷大之间的关系决定。蒸气压（P-sat）在T-inj。最后，发现关于空化数的C-d遵循几乎相同的线，即使在不同的P-无穷大时也是如此。这证实了在高燃料温度条件下发生的气穴现象取决于节流孔的下游压力，并且无论P-inj，P-infinity和P-inj为何，在高T-inj下气穴对Cd的影响都可以用气穴数很好地表示。 T-inj

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