軸流式渦輪葉片參數設計

A Ponametric Method of Axial Flow Turbine Blade Design

許文英(W. Y. Hsu) ； 陳世雄(S. H. Chen)

《中國航空太空學會學刊》 31卷3期 (1999/09) Pp. 223-230

https://doi.org/10.6124/TAASRC.199909_31(3).08

摘要

渦輪機械葉片三維幾何外形之決定直都是設計部門的一個瓶頸，也是在設計時程上必需不斷改進與增進效率的環節之一。本文主要在敘述如何運用少數關鍵翼剖面之基本幾可參數，如前、後緣中心線角度，前、後緣切圓半徑，前、後緣楔角，最大厚度值與其沿中心線所在位置等來設計渦輪葉片。文中將說明參數設計法之基本原理，並以一個多級渦輪組爲例作實際外形與參數設計結果做比對說明其優越性。

關鍵字

渦輪機 ； 葉片 ； 參數設計 ； 軸流

並列摘要

The determination of a three-dimensional turbomachinery blade configuration has always been a bottleneck in the design process. It is one of the major steps that require continuous improvement. The purpose of this paper is to describe the new parametric design approach that uses minimum key airfoil sectional parameters in turbine blade design. These' parameters are camber line angles at Leading edge (LE) and trailing edge (TE), radius at LB and TB, wedge angles at LE and TE, maximum thickness and its location along the camber line. The theory of the parametric design method will be discussed in detailed in the paper. A known multistage turbine configuration is used as an example to demonstrate the robustness of the present method.

並列關鍵字

turbomachine ； blade ； parametric design ； axial flow