超声速燃烧室壁面压力特征实验研究 *

推进技术 ›› 2018, Vol. 39 ›› Issue (7): 1633-1642.

超声速燃烧室壁面压力特征实验研究 *

浮强,宋文艳,王艳华,石德永,韩小宝

西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072

发布日期:2021-08-15
作者简介:浮强，男，博士生，研究领域为超燃冲压发动机。 E-mail: fqnwpu@mail.nwpu.edu.cn 通讯作者:宋文艳，女，博士，博士生导师，研究领域为超燃冲压发动机。
基金资助:
国家自然科学基金( 51506177)。

Experimental Investigationon WallPressure Characteristicin Hypersonic Combustor

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China and School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 为了评估基于燃烧室壁面压力实时监控的双模态超燃冲压发动机闭环控制系统方案的可行性，在西北工业大学地面直连式实验台上开展了一系列双模态超燃冲压发动机燃烧室地面直连式实验。实验模拟了飞行马赫数4.0条件下两个不同燃烧室构型点火燃烧的实际工作过程，测量并分析了燃烧室壁面压力脉动、压力响应和激波串前沿位置等特征。燃烧室进口来流状态为马赫数 2.0、总温约 880K、总压 0.8～1MPa。实验结果表明，燃烧室壁面压力存在明显脉动，且脉动幅度随着油气比的增加呈现增加趋势；壁面压力响应很快，响应时间在毫秒量级，说明在超燃冲压发动机闭环控制中，通过燃烧室实时壁面压力反馈来调节供油控制燃烧室工作状态是可能的；另外，通过改变燃油流量能够实时控制隔离段激波串前沿位置。

关键词: 超燃冲压发动机；燃烧室；闭环控制；压力响应

Abstract: To estimate the feasibility of a scramjet closed-loop control system which is based on the dualmode scramjet combustor wall pressure real-time monitoring，a series of dual mode scramjet combustor direct-connected experimental studies were conducted by using the direct-connected facility of Northwestern Polytechni.cal University(NWPU). The actual working process was simulated and two different scramjet combustor modelswere used. The characteristics of combustor wall pressure fluctuation，pressure response time and shock train lead.ing edge location are measured and analyzed. The typical flow conditions at combustor entrance are: Ma=2.0，to. tal-temperatureTt≈880K and total-pressurept=0.8～1MPa，which correspond to a Mach 4.0 flight condition. Ex.perimental results indicated that in scramjet combustor pressure fluctuation is obvious and pressure pulsation am.plitude will increase if the fuel supplies increase. Pressure response is soon，the response time is in millisecondsscale so it is possible to use wall pressure as the feedback parameter in the scramjet fuel supple closed-loop con.trol. Furthermore，the shock train leading edge location can be real-time controlled by adjusting the fuel flowrate.

Key words: Scramjet；Combustor；Closed-loop control；Pressure response

浮强,宋文艳,王艳华,石德永,韩小宝. 超声速燃烧室壁面压力特征实验研究 *[J]. 推进技术, 2018, 39(7): 1633-1642.

FU Qiang,SONG Wen-yan,WANG Yan-hua,SHI De-yong,HAN Xiao-bao. Experimental Investigationon WallPressure Characteristicin Hypersonic Combustor[J]. Journal of Propulsion Technology, 2018, 39(7): 1633-1642.

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