• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>ASME Turbo Expo vol.6 pt.A; 20050606-09; Reno-Tahoe,NV(US) >REDESIGN OF AN 11-STAGE AXIAL COMPRESSOR FOR INDUSTRIAL GAS TURBINE
【24h】

REDESIGN OF AN 11-STAGE AXIAL COMPRESSOR FOR INDUSTRIAL GAS TURBINE

机译：重新设计用于工业燃气轮机的11级轴流压缩机

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

Outlined in this paper are the details of redesign of an 11-stage axial compressor for 18MW class industrial gas turbine. Although the design value of adiabatic efficiency is 85%, the efficiency achieved in the prototype engine test was 1 point short of the target. According to the test results and CFD analyses, it was estimated that the stage mismatching due to an excessive work of intermediate stages was a major cause of the losses. To improve the matching, redesign of airfoils were carried out to some blades and vanes. The results of Multistage CFD showed that the matching was improved and the efficiency was increased, which was also confirmed by the engine test.
机译：本文概述了用于18MW级工业燃气轮机的11级轴向压缩机的重新设计细节。尽管绝热效率的设计值为85％，但原型发动机测试中达到的效率比目标低了1个百分点。根据测试结果和CFD分析，估计由于中间级的过度工作而导致的级不匹配是造成损失的主要原因。为了提高匹配度，对一些叶片和叶片进行了翼型的重新设计。多级CFD的结果表明，匹配得到了改善，效率得到了提高，发动机测试也证实了这一点。

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