首页> 外国专利> TURBINE AIRFOIL COOLING SYSTEM WITH NONLINEAR TRAILING EDGE EXIT SLOTS

TURBINE AIRFOIL COOLING SYSTEM WITH NONLINEAR TRAILING EDGE EXIT SLOTS

机译:带有涡轮尾缘出口的涡轮机翼冷却系统

摘要

A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel formed from a central trailing edge cooling channel and at least one trailing edge exit slot with a nonlinear longitudinal axis is disclosed. The trailing edge exit slot may be defined by ribs (24) having wavy side edges that form a jagged edge. As such, the nonlinear longitudinal axis (22) of the trailing edge exit slot reduces the effective flow area, generates impingement and turbulence to increase heat transfer and provides sufficient mechanical strength for better casting yield without overflowing for better performance. The nonlinear trailing edge exit slot may be formed using a ceramic core (106) and investment casting.
机译:公开了一种用于涡轮发动机的涡轮机翼的冷却系统,其具有由中央后缘冷却通道和至少一个具有非线性纵向轴线的后缘出口槽形成的后缘冷却通道。后缘出口狭槽可以由具有形成锯齿状边缘的波浪形侧边缘的肋(24)限定。这样,后缘出口狭槽的非线性纵向轴线(22)减小了有效流动面积,产生冲击和湍流以增加热传递,并提供了足够的机械强度以提供更好的铸件产量而不会溢流以提供更好的性能。可以使用陶瓷芯(106)和熔模铸造来形成非线性后缘出口狭槽。

著录项

  • 公开/公告号WO2015116325A3

    专利类型

  • 公开/公告日2015-10-29

    原文格式PDF

  • 申请/专利权人 SIEMENS AKTIENGESELLSCHAFT;SIEMENS ENERGY INC.;

    申请/专利号WO2014US70714

  • 发明设计人 LEE CHING-PANG;

    申请日2014-12-17

  • 分类号F01D5/18;B22C9/04;B22C9/10;B22C7/02;

  • 国家 WO

  • 入库时间 2022-08-21 15:04:59

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