...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Aerospace science and technology >Parallel rotor/stator interaction methods and steady/unsteady flow simulations of multi-row axial compressors
【24h】

Parallel rotor/stator interaction methods and steady/unsteady flow simulations of multi-row axial compressors

机译：平行转子/定子交互方法和多排轴流压缩机的稳定/不稳定流模拟

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

Rotor/stator interaction plays a crucial role in predicting the aerodynamic performance of high-speed multi-row axial compressor. Although mixing plane method has been widely used in steady simulations of multi-row single passage flows, the exchange of spanwise non-matched profiles of flow variable between adjacent blade rows is still unknown. Besides, quite little work was devoted to sliding mesh method for unsteady simulations of multi-row full-annulus compressor flows. In this work, mixing plane method and sliding mesh method were developed and presented, respectively, in the environment of parallel computer platforms. Particular attentions were paid to the accurate exchange of spanwise non-matched profiles of fluxes in mixing plane method, and the fast search algorithms of spanwise and circumferential non-matched meshes in sliding mesh method. The developed parallel rotor/stator interaction methods were validated with two multi-row high-speed axial compressors, i.e. NASA Stage 35 and first three stages of NASA 74A, both of which were calculated with steady flow simulation of one blade passage per row and unsteady flow simulation of full-annulus passages per row. Results highlighted that both the developed mixing plane method and sliding mesh method were able to predict the aerodynamic performance curve accurately and satisfy the interface flux conservation tightly. The flow wake and shock wave were observed to transfer continuously across rotor/stator interface with sliding mesh method in the unsteady full-annulus simulation. This work is valuable for the further development of advanced aerodynamic design and accurate performance prediction of multi-row axial compressors. (c) 2021 Elsevier Masson SAS. All rights reserved.
机译：转子/定子交互在预测高速多排轴向压缩机的空气动力学性能方面起着至关重要的作用。虽然混合平面方法已广泛用于多排单通流的稳定模拟，但是相邻刀片行之间的流量变量的始线不匹配轮廓的交换仍然未知。此外，致力于滑动网格方法，以进行多排全环压缩机流量的不稳定模拟。在这项工作中，在并行计算机平台的环境中分别开发和呈现混合平面方法和滑动网格方法。特别关注在混合平面方法中准确地交换助熔剂的助熔剂的助熔剂，以及滑动网格法中的始线和周向非匹配网格的快速搜索算法。用两个多排高速轴向压缩机（即NASA阶段35和NASA 74A的前三个阶段）验证了所开发的并联转子/定子相互作用方法，这两者都是用每行一个刀片通道的稳定模拟计算的，这两者都是计算的，并且不稳定每排全环通道的流量模拟。结果突出显示，发达的混合平面方法和滑动网格方法能够精确地预测空气动力学性能曲线，并紧紧满足界面磁通保存。观察到流动唤醒和冲击波在不稳定的全环模拟中连续地穿过转子/定子界面上连续传输。这项工作对于进一步开发先进的空气动力学设计和准确的多排轴流压缩机性能预测是有价值的。 （c）2021 Elsevier Masson SAS。版权所有。

著录项

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