首页> 外国专利> CHEVRON PLATFORM TURBINE VANE

CHEVRON PLATFORM TURBINE VANE

机译:雪佛兰平台涡轮叶片

摘要

Gas turbine vanes of a gas turbine vane assembly have a reconfigured platform shape so as to reduce the ingestion of hot combustion gases into platform gaps between adjacent vane assemblies is disclosed. The vane platforms are configured so the joint between adjacent vanes is repositioned a sufficient distance away from the leading edge of the vane airfoil and the associated bow wave generated by the hot combustion gases passing over the airfoil leading edge.
机译:公开了一种燃气涡轮机叶片组件的燃气涡轮机叶片,其具有重新构造的平台形状,从而减少了热燃烧气体被吸入相邻叶片组件之间的平台间隙中。叶片平台被构造成使得相邻叶片之间的接头被重新定位成与叶片翼型件的前缘和由通过翼型件前缘上方的热燃烧气体产生的相关联的弓形波足够的距离。

著录项

相似文献

  • 专利
  • 外文文献
  • 中文文献
获取专利

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