...
首页> 外文期刊>Aerospace science and technology >Numerical investigation on the assistant restarting method of variable geometry for high Mach number inlet
【24h】

Numerical investigation on the assistant restarting method of variable geometry for high Mach number inlet

机译:马赫数高的进气口可变几何辅助重启方法的数值研究

获取原文
获取原文并翻译 | 示例
   

获取外文期刊封面封底 >>

       

摘要

To compromise the compression efficiency and the starting properties, the inner contraction ratio (ICR) of a general high Mach number inlet is usually designed in the range of dual solution area. When going into an unstarted status, the high Mach inlet needs an assistant method to restart. This work explores a variable geometry method to restart the inlet. The rotating cowl is adopted to a typical Mach 4 cruising inlet, and the unsteady computation method with a dynamic Chimera grid technique is applied to simulate the rotating process of the inlet cowl. The change characteristics of the restarted performance at different rotating angle amplitude of the inlet cowl are investigated systematically. The numerical results reveal that the unstarted status of this typical inlet induced by the effect of high backpressure failed to restart if the inlet cowl rotating angle amplitude is under a small critical value, which is called lower critical angle. The inlet could restart if the cowl rotating angle amplitude is a little larger than the lower critical angle, and the flow may rapidly go to a steady condition after the inlet cowl returns to the design position. However, the performance of the restarted inlet is still worse than the design condition, because of the existence of an stable separation bubble on its shoulder, even if the inlet cowl stops rotating. The separation bubble becomes shrunk with an increasing the cowl rotating angle amplitude. When the inlet cowl rotating angle amplitude reaches a large critical value which is called upper critical angle, the separation bubble disappears, and all the separation is swallowed by the mean flow. Therefore the design performance of the inlet can be recovered, which means that the flow mass capture coefficient, total pressure recovery coefficient, drag and the outlet Mach number go back to the design level. It also shows that within the range of the lower and upper critical angles, the larger the rotating angle amplitude is, the more rapidly the separation bubble reaches stable state.
机译:为了损害压缩效率和起始性能,通常在双溶液面积的范围内设计一般的高马赫数入口的内部收缩率(ICR)。进入未启动状态时,高马赫进气口需要辅助方法才能重新启动。这项工作探索了一种可变几何方法来重新启动入口。典型的Mach 4巡航入口采用旋转整流罩,并采用动态Chimera网格技术的非稳态计算方法来模拟入口整流罩的旋转过程。系统地研究了进气罩不同旋转角度幅度下重启性能的变化特征。数值结果表明,如果进气罩的旋转角幅度处于较小的临界值(称为下临界角)以下,则由高反压效应引起的该典型进气口的未启动状态将无法重新启动。如果前围板旋转角度幅度比下临界角大一点,则可以重新启动入口,并且在前围板返回设计位置后,流量可能会迅速进入稳定状态。但是,重新启动的进气口的性能仍然比设计条件差,这是因为即使进气口前罩停止旋转,在其肩部上也会存在稳定的分离气泡。随着前围旋转角度幅度的增加,分离气泡收缩。当进气罩的旋转角度幅度达到一个较大的临界值(称为上临界角)时,分离气泡消失,所有分离被平均流量吞没。因此,可以恢复进气口的设计性能,这意味着流量捕获系数,总压力恢复系数,阻力和出气口马赫数可恢复到设计水平。它还表明,在下临界角和上临界角的范围内,旋转角幅度越大,分离气泡达到稳定状态的速度就越快。

著录项

  • 来源
    《Aerospace science and technology》 |2018年第8期|647-657|共11页
  • 作者

    Yuan Liu; Lu Wang; Zhansen Qian;

  • 作者单位

    AVIC Aerodynamics Research Institute,Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research;

    AVIC Aerodynamics Research Institute,Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research;

    AVIC Aerodynamics Research Institute,Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    High Mach number inlet; Assistant starting; Variable geometry; Chimera; Unsteady simulation;

    机译:马赫数高的进气口;辅助启动;可变的几何形状;嵌合体;不稳定的模拟;

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号