摘要
针对静子基元叶型低速模拟问题,分析了高低速转换过程的设计准则,提出对于静子叶型低速模拟需要保持出口气流角不变。根据设计准则,利用一维等熵假设,推导出基于低速叶型喉道宽度的约束模型,分析了关键设计参数的计算方法。利用分析结果,进行了一组高速静子CDA叶型的低速模拟,数值计算结果显示,低速模拟叶型的损失特性,落后角特性与高速原型趋势较为一致。分析发现喉道约束模型计算的喉道宽度与低速叶型实际值相对误差较小。在低速模拟过程中,喉道约束模型可以指导低速叶型最大厚度等参数的调整,从而减少设计迭代次数。
Some analyses of low-speed similarity design principles have been done for stator airfoils.It was proposed that the outlet flow angle should be kept unchanged for high-to-low speed transformation.Based on the design principles and a one-dimensional isentropic hypothesis,a constrained model of throat width for stator airfoils was derived,and the method of calculating geometry design parameters of low-speed airfoil was presented.According to the analysis results, a set of low-speed similarity transformation of high-speed stator CDA airfoil was carried out. The numerical results showed that the incidence-loss characteristics and incidence-deviation-angle characteristics had a good agreement for high and low speed airfoils.What's more,the relative error of throat width is small between the actual value and the value calculated by the throat constraint model.Therefore,the adjustment of parameters such as maximum thickness of low-speed blade could be guided by the throat constraint model,which could reduce the iterations of design low-speed airfoils.
作者
刘宝杰
张传海
于贤君
LIU Bao-Jie;ZHANG Chuan-Hai;YU Xian-Jun(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,Belting 100191,China;Collaborative Innovation Center of Advanced Aero-Engine,Beifing 100191,China)
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2019年第1期41-48,共8页
Journal of Engineering Thermophysics
基金
国家自然科学基金资助项目(No.51476004
No.51376014)
关键词
静子叶型
低速模拟
喉道约束模型
stator airfoils
low-speed similarity
throat constraint model