涡轮叶片二维冷却结构参数化设计技术研究

Parametric Design Method of 2D Turbine Blade Cooling Structure

研究了涡轮叶片二维冷却结构的参数化设计技术。采用参数控制点方法实现冷却叶片壁面的变厚度设计,采用隔肋数量、位置参数、偏转角度实现任意数量和形式的冷却腔造型,根据前缘缩进参数确定冷却通道前缘切线弧位置,通过尾缘切割参数实现半劈缝和全劈缝尾缘结构设计。结合叶片外形造型技术开发了造型设计程序,该程序可建立包含任意形式冷却通道和常用尾缘结构的变壁厚二维冷却叶片模型。

The parametric design method for 2D turbine blade cooling structure is studied. Parametric con- trolling point method is used to realize variable thickness design of blade wall. With the parameters of rib number, rib position and deflection angles, a variable number cooling chamber structure can be built. The retraction parameter decides the position of tangent circular arc at cooling passage leading edge. A division parameter is defined to get the trailing edge structure with whole slot or half slot. Then, combined with the blade profiles design technique, a 2D cooling turbine blade parametric design procedure is developed. With the procedure, a 2D turbine blade with variable thickness, including cooling passage in any forms and com- mon-used trailing edge can be easily built.