对转压气机叶排交界面参数传递的数值研究  

Numerical investigation of parameters transmission on blade rows interface of contra-rotating compressor

作　　者：邓小明[1,2] 高丽敏[1,2] 高磊[1,2] 蔡宇桐 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2015年第6期1460-1469,共10页Journal of Aerospace Power

基　　金：国家自然基金重点项目(51236006);西北工业大学基础研究基金(JC201141);新世纪优秀人才支持计划(NCET-10-0078)

摘　　要：针对超常规叶轮机械——对转压气机采用5种定常叶排交界面方法,结合实验值对比分析了对转压气机整机性能、近设计工况以及近失速工况流场,以定量研究不同交界面方法应用于叶排交界面的参数传递效果.结果表明:1不同交界面方法计算的整机效率性能差异明显,而压比性能与实验值吻合较好.2近设计工况下,周向守恒法在不同交界面的参数传递连续性相对较好,当地守恒法和完全非匹配混合界面法对下游界面参数的控制作用逐渐增强,一维无反射边界条件和完全非匹配冻结转子法则正好相反.3近失速工况下,一维无反射边界条件和完全非匹配冻结转子法对应的叶片前缘高熵损失区范围明显增大,叶顶主流和间隙溢流交界面扭曲成更靠近上游叶排交界面的弧形.Five steady blade rows interface methods were adopted to investigate an extraordinary turbomachinery—contra-rotating compressor.The whole performance,near design condition and near stall condition flow field of contra-rotating compressor were analyzed in combination with experimental data,so as to make a quantitative comparison of the effect on blade row interface parameters transmission among different interface methods.Results validate：（1）the whole compressor efficiency shows obvious difference among different interface methods,while the pressure ratio agrees with experimental data very well.（2）Under the near design condition,the parameters transmission on different interfaces are uniform for conservative coupling by pitchwise rows method.Local conservative coupling method and matching mixing plane methods behave better along downstream interface,while non reflecting 1-D method and full non matching frozen rotor method perform just the opposite.（3）Under the near stall condition,the high entropy loss area surrounding blade leading edge of non reflecting 1-D method and full non matching frozen rotor method expands much bigger.Mainstream and overflow interface within the blade tip twists into an arc closer to the upstream blade row interface.

关 键 词：参数传递 对转压气机 多级叶排 交界面方法 整机性能 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]