摘要
为评估安装于某型飞机的某涡桨发动机吹风流场,针对其装机状态,采用UG软件建立实体模型及流域计算模型,采用ICEM软件对流域进行网格划分,采用Fluent软件进行吹风流场稳态数值模拟,湍流模型选择S-A模型,转动域及静止域采用动参考系模型进行参数传递。为验证计算模型及计算方法的准确性,对发动机吹风流场的关键点风速进行了试验测量,结果表明:无量纲速度差基本在0.15内,单发在4.32m高处无量纲速度差0.17,双发在6m高处无量纲速度差0.3,吻合程度较好。验证了计算模型、计算方法的可行性,可进一步推广应用。
In order to evaluate the blowing flow field of a turboprop engine installed in a aircraft,the solid model and fluid domain calculation model were established by using UG software according to the installed state of the turboprop engine.Fluid domain grid division was carried out by ICEM software.Steady -state numerical simulation of blowing flow field was carried out by Fluent software.The turbulence model selected the S-A model.Parameter transfer was carried out for the rotational domain and the static domain by using the dynamic reference system model.In order to verify the accuracy of the calculation model and calculation method,the test measurement was carried out for the key wind speed of the engine blowing flow field.The results show that the dimensionless velocity difference is basically in the range of 0.15,the dimensionless velocity difference is 0.17 at the height of 4.32 m for single engine,the dimensionless velocity difference is 0.3 at the height of 6 m for double engine,and the degree of anastomosis is good.The feasibility of the calculation model and the calculation method is verified,which can be further popularized and applied.
作者
孙科
丁旭
王欢
许思琦
SUN Ke;DING Xu;WANG Huan;XU Si-qi(Chinese Flight Test Establishment,Xi'an 710089,China)
出处
《航空发动机》
北大核心
2019年第5期82-86,共5页
Aeroengine
基金
航空动力基础研究项目资助
