航空学报 > 2014, Vol. 35 Issue (1): 125-131   doi: 10.7527/S1000-6893.2013.0372

基于膨胀度可控的SERN设计及试验验证

赵强, 徐惊雷, 于洋   

  1. 南京航空航天大学 能源与动力学院, 江苏 南京 210016
  • 收稿日期:2013-03-28 修回日期:2013-08-26 出版日期:2014-01-25 发布日期:2013-08-28
  • 通讯作者: 徐惊雷,Tel.:025-84892204 E-mail:xujl@nuaa.edu.cn E-mail:xujl@nuaa.edu.cn
  • 作者简介:赵强 男,硕士研究生。主要研究方向:高超声速内流气体动力学。E-mail:chikeeyzq@126.com;徐惊雷 男,教授,博士生导师。主要研究方向:高超声速进排气气动力学。Tel:025-84892204 E-mail:xujl@nuaa.edu.cn
  • 基金资助:

    国家自然科学基金(90916023)

Design and Experimental Validation of SERN Based on Controllable Expansion Degree Distribution

ZHAO Qiang, XU Jinglei, YU Yang   

  1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2013-03-28 Revised:2013-08-26 Online:2014-01-25 Published:2013-08-28
  • Supported by:

    National Natural Science Foundation of China (90916023)

摘要:

单边膨胀喷管(SERN)是超燃冲压发动机的关键部件,由于其几何非对称,在发动机点火/熄火瞬间,SERN会产生较大的冷热态俯仰力矩差,影响飞行器的稳定性。现有解决方法主要是利用几何/气动调节方式,但都有不利影响。本文提出了基于膨胀度可控的SERN设计的新方法,将采用该方法得到的喷管模型B与基准喷管模型A进行了对比研究,并对模型B进行缩比冷流试验,试验与数值模拟结果吻合良好。研究结果表明:飞行马赫数为4.5时,模型B的推力系数比模型A仅仅下降了0.1%,而模型B比模型A的冷热态俯仰力矩差减小了80.49%;飞行马赫数为6.5时,模型B的推力系数比模型A不仅上升1.1%,同时模型B比模型A冷热态俯仰力矩差还下降12.73%,验证了设计思想的正确性,为提高SERN俯仰力矩性能提供了一种新的思路。

关键词: 单边膨胀喷管, 俯仰力矩差, 膨胀程度, 风洞试验, 推力系数

Abstract:

The single expansion ramp nozzle (SERN) is a key component of a scramjet engine. However, because of its asymmetrical geometry large pitch moment differences exist from the SERN at the start and shut-down moment of the scramjet engine, which seriously affects the stability of the aircraft. To overcome the shortcomings of the existing methods of reducing pitch moment differences which use adjustable nozzles, a nozzle Model B based on controllable expansion degree distribution is presented in this paper. Model B compares with baseline Model A. Cold-flow test and numerical simulation are conducted on the sub-scaled Model B, and their results agree well with each other. The results demonstrate that at flight Mach numbers 4.5 and 6.5, the pitch moment of the cold-state and hot-state of Model B decreases by 80.49% and 12.73% respectively, while the thrust coefficient decreases by 0.1% at flight Mach number 4.5 and increases by 1.1% at flight number 6.5. The pitch moment performance of the SERN is improved significantly, which effectively reduces the difficulty of the aircraft trim. The validity of the design thinking and method is fully verified, which provides a new approach for improving the pitch moment performance of the SERN.

Key words: single expansion ramp nozzle, pitch moment difference, expansion degree, wind tunnel experiment, thrust coefficient

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