环管形燃烧室燃气导管造型计算方法

NUMERICAL MODELLING FOR GAS DUCT IN TUBOANNULAR COMBUSTOR

本文对航空燃气轮机环管形燃烧室火焰筒燃气导管造型问题进行了研究。给出了一种基于沿轴向面积变化规律、上下素线和上下圆弧半径变化规律的半经验剖切造型计算方法。应用这种方法 ,以斯贝发动机燃气导管为例进行了计算。

A numerical approach to modelling of hot gas duct in tuboannular combustor is suggested.The modelling scheme is based on five controlling rules:top and bottom curves on central profile,radii of top and bottom arcs of cross sections,and area of cross sections.A three dimensional hot gas duct is regarded as a stacking of finite two dimensional cross sections constrained by the rules.A brief analysis of computed rules is presented as well.As an example the hot gas duct of SPEY engine is computed by using this method.Comparison between the computed cross sections and real ones obtained from SPEY technical drawings shows that the method is effective and practicable.