摘要
针对在多级涡轮流道中沿流动方向燃气温度变化较大这一特点，为了准确反映出温度变化对气动热力计算结果的影响，提出了一种考虑变比热影响的Ｓ２流面的气动热力计算方法。该方法摒弃了传统的定比热气动热力计算公式和由温度、密度确定压力的求解顺序，而是根据导出的变比热计算压力的关系式求解压力，然后用温度和压力计算密度。计算结果显示出本文的算法较传统的未能充分考虑变比热影响的气动热力计算方法可以改善多级涡轮联算时的计算准确度。
In accordance with large temperature gradient in multi-stage turbine channel,an aerothermodynamic method is proposed for varying specific heat solution of S 2 surface to consider precisely the effect of temperature variation on the computed results.Usually,in S 2 calculation,a traditional aerothermodynamic method is unable to take full influence of the varying specific heat into account.In the proposed method the pressure is calculated with an integration relation of Gibbs identity along streamlines under the condition of varying specific heat and then the density may be determined by the pressure and temperature.Some computed results of a 2-stage gas turbine show that as compared with the traditional aerothermodynamic method,the new method can improve the accuracy of joint computation for multi-stage turbines.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1996年第1期11-14,共4页
Journal of Aerospace Power
基金
国家自然科学基金
关键词
涡轮
气体动力学
热力计算
多级涡轮
S流面
Turbines Gasdynamics Thermodynamic calculations Computational methods
