• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文学位 >VORTEX SHEDDING FROM SOLID ROCKET MOTOR PROPELLANT INHIBITORS (FREQUENCY, COMPUTATIONAL FLUID DYNAMICS).
【24h】

VORTEX SHEDDING FROM SOLID ROCKET MOTOR PROPELLANT INHIBITORS (FREQUENCY, COMPUTATIONAL FLUID DYNAMICS).

机译：固体火箭发动机推进剂抑制剂的涡旋破碎（频率，计算流体动力学）。

获取原文
获取原文并翻译 | 示例
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A mathematical model is presented for investigating the vortex shedding caused by the protrusion of inhibitors into the flow field of a solid rocket motor (SRM). The principal objective of the research is the theoretical determination of the vortex shedding frequency. For the model, the time-dependent Navier-Stokes equations are solved with the assumption of incompressible, two-dimensional flow using a finite difference technique. For laminar flow, explicit solutions are obtained using a vorticity-transport equation in place of the Navier-Stokes equations. A two-equation ((kappa)-(epsilon)) model is used for turbulence modeling. The solutions are obtained from primitive equations using a semi-implicit, pressure-correction method.; To verify the theoretical results, cold flow tests were conducted to determine experimentally the vortex shedding frequency under both laminar and turbulent flow conditions. The laminar flow experimental model is two-dimensional and was tested at Reynolds numbers from 2.72 x 10('4) to 8.05 x 10('4) in the Auburn University smoke tunnel. The turbulent flow model is an axisymmetric 2.6% scale model of a section of the Space Shuttle SRM containing circular perforated grain segments and inhibitors made to simulate the geometry after 80 seconds of burning. This model was tested in the Auburn University supersonic wind tunnel test facility at Reynolds numbers from 2.45 x 10('5) to 5.97 x 10('5). For both laminar and turbulent flow models, the vortex shedding frequencies were determined using a stroboscope and yarn tufts fastened to one inhibitor. Upstream conditions were measured by hot wire and hot-film anemometers for laminar and turbulent flow, respectively.; The vortex frequencies measured compared favorably with those obtained from the mathematical model. The range of these frequencies was about from 5 HZ to 30 HZ. The frequencies were sensitive to upstream turbulence intensity. The location of the vortex shedding, which existed behind the inhibitors of the experimental models agreed reasonably well with predictions from the mathematical models for both laminar and turbulent flow.
机译：提出了一个数学模型，用于研究由抑制剂进入固体火箭发动机（SRM）的流场引起的涡流脱落。该研究的主要目标是涡旋脱落频率的理论确定。对于该模型，使用有限差分技术，在假设不可压缩的二维流动的前提下，求解时间相关的Navier-Stokes方程。对于层流，使用涡度传输方程代替Navier-Stokes方程获得显式解。二方程（（κ）-（ε））模型用于湍流建模。解决方案是使用半隐式压力校正方法从原始方程式获得的。为了验证理论结果，进行了冷流测试，以实验确定层流和湍流条件下的涡旋脱落频率。层流实验模型是二维的，并在奥本大学烟雾隧道中以雷诺数从2.72 x 10（'4）到8.05 x 10（'4）进行了测试。湍流模型是航天飞机SRM截面的轴对称的2.6％比例模型，其中包含圆形穿孔的颗粒段和抑制剂，在燃烧80秒后可以模拟几何形状。该模型在奥本大学超音速风洞测试设备中以2.45 x 10（'5）至5.97 x 10（'5）的雷诺数进行了测试。对于层流模型和湍流模型，使用频闪观测仪确定涡旋脱落频率，并将纱线簇固定在一个抑制剂上。上游条件分别通过热线和热膜风速计测量层流和湍流。与从数学模型获得的涡旋频率相比，测量的涡旋频率具有优​​势。这些频率范围约为5 HZ至30 HZ。频率对上游湍流强度敏感。存在于实验模型抑制器后面的涡流脱落位置与层流和湍流数学模型的预测非常吻合。

著录项

  • 作者

    SHU, PING-HUEI.;

  • 作者单位

    Auburn University.;

  • 授予单位 Auburn University.;
  • 学科 Engineering Aerospace.
  • 学位 Ph.D.
  • 年度 1985
  • 页码 85 p.
  • 总页数 85
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航空、航天技术的研究与探索;
  • 关键词

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