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首页> 外文期刊>Advances in Aircraft and Spacecraft Science >Effect of control route on the unstart/restart characteristics of an over-under TBCC inlet
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Effect of control route on the unstart/restart characteristics of an over-under TBCC inlet

机译：控制路线对TBCC进气不足的起动/重启特性的影响

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摘要

Numerical simulations have been conducted to study the unstart/restart characteristics of an over-under turbine-based combined-cycle propulsion system (TBCC) inlet during the inlet transition phase. A dual-solution area exists according to the Kanlrowitz theory, in which the inlet states may be different even with the same input parameters. The entire transition process was divided into five stages and the unstanVrestart hysteresis loop for each stage was also obtained. These loops construct a hysteresis surface which separates the operating space of the engine into three parts: in which a) inlet can maintain a started state; b) inlet keeps an unstarted state; c) inlet state depends on its initial state. During the transition, the operation of the engine follows a certain order with different backpressures and splitter angles, namely control route, which may result in disparate inlet states. Nine control routes with different backpressures and transition stages were designed to illuminate the route-dependent behavior of the inlet The control routes operating towards the unstart boundary can make the inlet transit from a started state into an unstarted one. But operating backward the same route cannot make the inlet restart, additional effort should be made.
机译：已经进行了数值模拟，以研究进气过渡阶段过基于涡轮的联合循环推进系统（TBCC）进气的启动/重启特性。根据Kanlrowitz理论，存在双解区域，其中即使输入参数相同，入口状态也可能不同。整个过渡过程分为五个阶段，并且还获得了每个阶段的unstanVrestart磁滞回线。这些回路构成了一个磁滞表面，该表面将发动机的工作空间分为三个部分：a）进气口可以保持启动状态； b）入口保持未启动状态； c）入口状态取决于其初始状态。在过渡期间，发动机的运行遵循一定的顺序，具有不同的背压和分流角，即控制路径，这可能会导致进气状态不同。设计了九个具有不同背压和过渡阶段的控制路径，以阐明入口的路径相关行为。朝着未启动边界运行的控制路径可使入口从启动状态过渡到未启动状态。但是，以相同的路线向后操作无法使进气口重新启动，应该付出额外的努力。

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  • 来源
    《Advances in Aircraft and Spacecraft Science》 |2018年第4期|431-444|共14页
  • 作者

    Nan Li; Juntao Chang; Jingfeng Tang; Daren Yu; Wen Bao; Yanping Song;

  • 作者单位

    Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute of CARDC, Sichuan, Mianyang 621000, People's Republic of China,Harbin Institute of Technology, Harbin, Heilongjiang 150001, People's Republic of China;

    Harbin Institute of Technology, Harbin, Heilongjiang 150001, People's Republic of China;

    Harbin Institute of Technology, Harbin, Heilongjiang 150001, People's Republic of China;

    Harbin Institute of Technology, Harbin, Heilongjiang 150001, People's Republic of China;

    Harbin Institute of Technology, Harbin, Heilongjiang 150001, People's Republic of China;

    Harbin Institute of Technology, Harbin, Heilongjiang 150001, People's Republic of China;

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  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    inlet mode transition; unstart/restart hysteresis; control route; route-dependent;

    机译：进气模式转换;取消/重启磁滞;控制路线;路线相关;

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