• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>Proceedings of the 1st International Symposium on Jet Propulsion and Power Engineering >IMPROVED DESIGN AND ANALYSIS OF A CENTRIFUGAL COMPRESSOR WITH LARGE ATTACK ANGLE
【24h】

IMPROVED DESIGN AND ANALYSIS OF A CENTRIFUGAL COMPRESSOR WITH LARGE ATTACK ANGLE

机译：大攻角离心压缩机的改进设计与分析

获取原文
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

In order to improve the performance of a centrifugal compressor in an air turbine expander, the impeller of it was improved in this paper. Considering to improve efficiency of the impeller and reduce difficulty in producing it, and in order to compare the difference of the flow conditions between impellers with different inlet angles, three impellers with inlet angles 43°,50°, 56° were designed in this paper, and their attack angles were 15°, 8°, 2° at the design point. The newly designed impellers were only changed the inlet angles while their other parameters were same to the original impeller. Numerical simulation of the four compressors were made by using Reynold averaged Navier-Stokes equations, and their characteristic lines were calculated in this paper. Especially the flow fields inside the impellers were analyzed in detail. The analysis shows that there are terrible separate flows in the original impeller and as the inlet angle increases the flow conditions are improved. It is concluded that the efficiencies, the pressure ratios and the stability ranges of the three newly designed impellers are all increased and the impeller with 56° inlet angle has the highest efficiency and pressure ratio.
机译：为了提高空气涡轮膨胀机中离心压缩机的性能，本文对其叶轮进行了改进。为了提高叶轮效率，减少制造难度，为了比较不同进口角的叶轮之间的流动条件差异，设计了三个进口角为43°，50°，56°的叶轮。 ，它们在设计点的迎角分别为15°，8°，2°。新设计的叶轮仅改变了进气角度，而其他参数与原始叶轮相同。利用雷诺平均Navier-Stokes方程对这4台压缩机进行了数值模拟，并计算了它们的特性线。特别是对叶轮内部的流场进行了详细分析。分析表明，原始叶轮中存在单独的流动不良，并且随着进口角的增加，流动条件得到改善。结论是，三个新设计的叶轮的效率，压力比和稳定性范围都得到了提高，并且入口角为56°的叶轮具有最高的效率和压力比。

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