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IMPROVEMENTS TO THE THERMAL BEHAVIOUR OF THE TRAILING EDGE OF A HIGH PRESSURE TURBINE BLADE

机译:高压透平叶片尾缘热性能的改进

摘要

portable high-pressure turbine. in turbomachine, comprising at least one cooling system comprising at least one cavity radially extending between a top and a bottom of the dawn.at least one air inlet opening at one end of the ring cavity for the cooling circuit and the cooling air.and a plurality of apertures (26) which opens in the cavity and on the trailing edge of dawn, the slits is installed along the trailing edge.between the base and the top of the morning, a substantially perpendicular to a longitudinal axis of the dawn.at least the slot (28) closest to the foot of the dawn with a slope to the top of the sun between 10 and 30 degrees relative to the axis of rotation of the sun.
机译:便携式高压涡轮机。在涡轮机中,包括至少一个冷却系统,该冷却系统包括至少一个在黎明的顶部和底部之间径向延伸的腔;在环形腔的一端的至少一个进气口,用于冷却回路和冷却空气。在空腔中并且在黎明的后缘上开口的多个孔(26),狭缝沿着后缘安装。在早晨的底部和顶部之间,基本上垂直于黎明的纵轴。至少最靠近黎明脚的槽(28)相对于太阳的旋转轴到太阳顶部的倾斜度在10到30度之间。

著录项

  • 公开/公告号CA2412989C

    专利类型

  • 公开/公告日2008-09-23

    原文格式PDF

  • 申请/专利权人 SNECMA MOTEURS;

    申请/专利号CA20022412989

  • 发明设计人 BOURY JACQUES;BARIAUD CHRISTIAN;

    申请日2002-11-29

  • 分类号F01D5/18;

  • 国家 CA

  • 入库时间 2022-08-21 20:03:57

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