Abstract: A numerical method is presented for simulating turbomachinery blade rows in multistage turbine by a steady three dimensional Navier Stokes solver. The principal assumptions are that the flow is steady relative to each blade row individually and that the rows can communicate via inter row mixing planes. These mixing planes introduce circumferential averaging of flow properties but preserve circumferential variations in the blade row and general radial variations. Varying specific heat was adopted in this method in order to consider wide tempter rages of multistage turbine. An application is present in a NASA test. In this case,the results of calculation are in much closer agreement with the experimental evidence.

Key words: Three dimensional flow;Viscous flow;Multistage gas turbine;Mixing plane +;Numerical calculation

摘要： 给出了一种可以在多级透平环境中模拟三维粘性流动的数值方法，这种方法在各叶栅排作了相对定常流动的假设， 各叶栅排间通过“混合平面”传递参数。“混合平面”间传递周向平均的气动参数， 但保持了径向参数的变化和本列参数的周向不均匀性， 同时考虑了变比热容对多级透平计算的影响。通过对一ＮＡＳＡ 透平级的计算， 证实计算结果不仅和实验结果吻合的非常好， 而且很好地描述了流动的粘性效应和透平级内的涡结构

关键词: 三维流;粘性流;多级燃气涡轮;混合平面;数值计算