亚/超临界多相煤油喷嘴流量特性

朱珈驹; 惠鑫; 刘桂桂; 薛鑫; 杨越; 黎家驹

doi:10.13224/j.cnki.jasp.20220271

亚/超临界多相煤油喷嘴流量特性

doi: 10.13224/j.cnki.jasp.20220271

朱珈驹^{1, 3,},
惠鑫^{1, 3},
刘桂桂^{2, 3},
薛鑫^{1, 3,*, ,},
杨越^{2, 3},
黎家驹^{2, 3}

1.
北京航空航天大学航空发动机研究院，北京 100191
2.
北京航空航天大学能源与动力工程学院，北京 100191
3.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 100191

基金项目: 国家科技重大专项（2017-Ⅲ-0005-0029）

详细信息

作者简介:
朱珈驹（1998-），男，硕士生，主要研究领域为超临界航空煤油喷射燃烧

通讯作者:
薛鑫（1983-），男，助理研究员，博士，主要研究领域为航空发动机燃烧室。E-mail：xinxue@buaa.edu.cn

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2022-04-29
- 网络出版日期: 2022-09-07

Mass flow rate characteristics of sub-/supercritical multiphase kerosene fuel nozzle

ZHU Jiaju^{1, 3
,},
HUI Xin^{1, 3},
LIU Guigui^{2, 3},
XUE Xin^{1, 3,*
, ,},
YANG Yue^{2, 3},
LI Jiaju^{2, 3}

1.
Research Institute of Aero-Engine，Beihang University，Beijing 100191，China
2.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
3.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics，Beihang University，Beijing 100191，China

摘要

摘要:
为了精确设计多相煤油喷嘴，以应用于采用冷却涡轮冷气技术的航空发动机，采用轴对称的模拟喷嘴，在不同的固定喷射压力下，通过调节燃油温度，获得了亚/超临界的燃油流量变化规律。根据煤油相态的分区理论，将流量曲线分为液相区、气液两相区和超临界区，分析不同相态航空煤油流量随喷射状态变化的作用机制，分别给出液相区和超临界区的流量计算方法及气液两相区流量系数的拟合关系式。结果表明：在喷射温度从常温至750 K的范围内，流量在液相区缓慢降低，在气液两相区加速下降，最后经“拐点”温度后进入超临界区缓慢下降。计算结果与试验值最大误差为3.8%，拟合式的相关系数平方为0.9478，该结果可作为多相喷嘴设计的计算依据。同时获得的流量数据，可以作为喷嘴下游喷射结构的研究的边界条件，支撑先进航空发动机设计研发。
- 流量特性 /
- 亚/超临界喷射 /
- RP-3航空煤油 /
- 燃油喷嘴 /
- 闪蒸 /
- 数值等熵加速法
Abstract:
To precisely design multiphase fuel nozzles, so that they can be applied to the aero-engines with the technology of cooling the turbine cooling air, the fuel mass flow rate of sub-/supercritical kerosene in an axisymmetric model nozzle was studied. By adjusting the fuel temperature under multiple sets of fixed injection pressure, the mass flow rate change of sub-/supercritical fuel was obtained. According to the phase conditions of kerosene, the flow rate curves were divided into three phase regimes, i.e., liquid, gas-liquid, and supercritical, and the mechanisms in the process of flow rate changing with kerosene injection status under different phase conditions were discussed. The flow rate prediction methods in the liquid and the supercritical regime, as well as the fitting correlation of the discharge coefficient in the gas-liquid regime, were proposed. Results showed that, as injection temperature increased from normal temperature to 750 K, the flow rates slowly decreased in the liquid regime, sharply declined in the gas-liquid regime, and then gradually declined in the supercritical regime beyond the “inflection point” temperature. The maximum error between the calculated and experimental results was 3.8%, and the square of the correlation coefficient of the fitting correlation was 0.9478, which can serve multiphase nozzle design. Meanwhile, the acquired mass flow rate data can provide the boundary conditions for the research of injection structures downstream the nozzles, supporting advanced aero-engine design and development.
- mass flow rate characteristics /
- sub-/supercritical injection /
- RP-3 aviation kerosene /
- fuel nozzle /
- flash boiling /
- numerical method of isentropic acceleration

HTML

图 1 试验系统图

Figure 1. Schematic diagram of the experiment system

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图 2 喷嘴实物图及流道示意图（单位：mm）

Figure 2. Applied nozzle and its flow path schematic diagram （unit：mm）

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图 3 RP-3替代燃料的s-p相图

Figure 3. s-p diagram of RP-3 surrogate

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图 4 亚/超临界多相RP-3煤油流量特性

Figure 4. Mass flow rate characteristics of sub-/supercritical multiphase RP-3 kerosene

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图 5 流量曲线1阶、2阶导数

Figure 5. First and second derivative of the mass flow rate curve

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图 6 RP-3替代燃料的p-T相图

Figure 6. p-T diagram of RP-3 surrogate fuel

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图 7 RP-3替代燃料的密度特性

Figure 7. Density characteristics of RP-3 surrogate

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图 8 密度曲线1阶、2阶导数

Figure 8. First and second derivative of the density curve

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图 9 归一化密度特性和流量特性

Figure 9. Normalized characteristics of density and mass flow rate

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图 10 RP-3替代燃料的黏度特性

Figure 10. Viscosity characteristics of RP-3 surrogate

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图 11 喷嘴流量系数随喷射工况的变化

Figure 11. Changes of nozzle discharge coefficient with injection condition

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图 12 “拐点”温度的计算值及其线性拟合结果

Figure 12. Calculated values of “inflection point” temperature and their linear fit

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图 13 液相区流量计算值与试验值比较

Figure 13. Comparison of the calculated and experimental values of mass flow rate in liquid regime

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图 14 超临界区流量计算值与试验值比较

Figure 14. Comparison of the calculated and experimental values of mass flow rate in supercritical regime

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图 15 气液两相区流量系数拟合曲线

Figure 15. Fitting curve of discharge coefficient in gas-liquid regime

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表 1 试验工况

Table 1. Experiment conditions

参数数值

p_c/MPa 2.4
T_c/K 660
p_r 0.85～1.35
T_r 0.454～1.14
p_amb/MPa 0.1

下载: 导出CSV

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