低速风洞引射短舱动力模拟技术新进展

发布时间：2018-03-17 16:49

本文选题：引射短舱　切入点：动力模拟　出处：《空气动力学学报》2016年06期 　论文类型：期刊论文

【摘要】：引射短舱可以模拟发动机短舱的喷流影响,并部分模拟进气影响,能用于研究发动机短舱与机翼及增升装置的气动干扰特性,且具有研制周期短、造价低等特点,是在风洞中开展飞机/发动机一体化设计研究的一种重要试验技术。本文介绍了气动中心低速所在引射短舱设计技术和试验技术方面的新进展。采用商业软件对引射短舱进行了三维流场数值模拟,获得了引射短舱性能和三维流场信息。对引射短舱内部流场进行了分析和研究,对引射喷嘴数量、位置进行了优化,增加了引射短舱的进气流量,改善了尾喷口流场均匀度,明显提高了引射短舱性能。发展了空气桥技术,采用有限元方法进行了优化设计,对空气桥和天平进行一体化设计,并进一步发展了空气桥影响修正技术,解决了供气管路对天平测力的影响问题。发展了高精度流量测量控制技术,采用了数字阀、流量控制单元、短舱内部测量耙等技术,提高了流量的控制测量精度及测量不确定度,流量控制精度达到了0.1%,流量测量不确定度达到了0.3%,引射短舱落压比控制精度优于0.01。研制了短舱移动支撑装置,能够实现引射短舱的独立支撑,并实现短舱前后和上下位置的变化,用于开展短舱位置优化研究。最后,介绍了引射短舱的地面性能测试及风洞试验应用,给出了性能测试与数值模拟的对比结果和典型的风洞试验结果,试验结果表明动力影响使得飞机0°迎角升力减小,升力线斜率增大,失速迎角推迟。
[Abstract]:The ejector can simulate the jet effect of the engine chamber and partly simulate the air intake effect. It can be used to study the aerodynamic interference characteristics of the engine cabin, the wing and the lifting device, and has the characteristics of short development period and low cost. It is an important test technology for the research of aircraft / engine integrated design in wind tunnel. This paper introduces the new development of design technology and test technology of ejector in low speed pneumatic center. The three-dimensional flow field of the ejector is numerically simulated. The internal flow field of the ejector is analyzed and studied, the number and position of the ejector nozzle are optimized, the inlet flow rate of the ejector is increased, and the uniformity of the flow field of the tail nozzle is improved. The air bridge technology is developed, the finite element method is used to optimize the design, the air bridge and balance are designed integratively, and the influence correction technology of air bridge is further developed. The problem of the influence of air supply line on the balance force measurement is solved. The high precision flow measurement control technology is developed, and the digital valve, flow control unit, short cabin internal measuring rake and so on are adopted. The accuracy and uncertainty of flow control are improved. The accuracy of flow control is 0.1, the uncertainty of flow measurement is 0.3, the control precision of drop pressure ratio of ejector is better than 0.01. It can realize the independent support of the ejector, and the change of the position before and after, up and down, which can be used to carry out the optimization research of the short cabin. Finally, the ground performance test of the ejector and the application of the wind tunnel test are introduced. The comparison between performance test and numerical simulation and typical wind tunnel test results are given. The experimental results show that the lift force at 0 掳angle of attack decreases, the slope of lift line increases and the stall angle of attack is delayed.
【作者单位】：中国空气动力研究与发展中心低速空气动力学研究所;
【分类号】：V211.74

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