Design and experimental investigation of ejector based on high temperature gas ejection
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摘要: 结合气体热力学理论和等压引射器设计理论方法，提出了高温燃气热力学参数计算方法，研制了基于高温燃气引射的超声速引射器试验平台。通过引射器与燃气发生器的对接实验，研究了零引射和被引射气流引射两种状态下的工作性能以及引射气流温度变化对工作性能的影响。实验结果表明：被引射气流流量360 g/s时，入口总压达到3.89 kPa，优于设计指标4 kPa；引射气流温度在低于设计值100 K范围内的变化对引射器的工作性能不会造成影响。实验验证了基于高温燃气引射的超声速引射器性能计算分析与工程设计方法的可靠性，相关研究结果为燃气发生器参数优化提供了指导性建议。Abstract: Combining the gas thermodynamics with the isobaric ejector design theory, the calculation method of thermodynamic parameters of high temperature gas is presented, and the ejector design scheme based on the high temperature gas ejection is proposed. Through the docking experiment between the ejector and the gas generator, the working performance of zero injection and secondary flow are studied, and the influence of temperature change of ejected gas flow on the working performance are also studied. The experimental results show that the total inlet pressure can reach 3.89 kPa with the secondary flow at 360 g/s, and the variation of the ejector gas temperature within 100 K below the design point has no effect on the ejector performance, which verifies the reliability of performance calculation analysis and engineering design method of the supersonic ejector based on high temperature gas injection, and the relevant research results provide guidance suggestions for parameter optimization of the gas generator.
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Keywords:
- supersonic /
- ejector /
- gas generator /
- zero ejection /
- secondary flow
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表 1 引射器设计参数
Table 1 Design parameters of the ejector
引射马赫数Ma 引射气流总压pt1/MPa 引射流量g/(kg·s-1) 引射气流总温Tt1/K 引射系数k 一级引射器 5.0 2.41 0.62 800 0.581 二级引射器 3.9 2.83 2.61 900 0.375 
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表 2 实验结果与设计值对比
Table 2 Comparison of experimental results and design values
一级引射器 二级引射器 被引射气流压力pt2/kPa 总引射系数ktotal 总增压比εtotal 引射压力pt1/MPa 引射温度Tt1/K 引射压力pt1/MPa 引射温度Tt1/K 设计值 2.41 800 2.83 900 4.00 0.111 25.00 实验值 2.38 790 2.87 910 3.89 0.110 24.94
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表 3 燃气发生器实验结果
Table 3 Experimental results of the gas generator
空气流量mair/(kg·s-1) 酒精流量malc/(g·s-1) 空燃比AF 燃气温度T/K 设计值 23.2 800 29.0 1100 实验值 23.5 776 30.3 1080
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表 4 不同引射气流温度的实验结果
Table 4 Experimental results of different ejection flow temperatures
空气供应压力pair /MPa 酒精喷前压力pj /MPa 一级集气室温度T1/K 二级集气室温度T2/K 引射气流总压pt1/kPa 4.5 6.5 697 806 3.90 4.5 7.0 710 834 3.89 4.2 8.0 790 910 3.89 4.0 8.0 808 946 3.90
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