摘要
基于求解三维雷诺平均N-S方程,采用混合平面法并应用微机网络并行计算技术,结合Spalart-Allamaras一方程湍流模型,对某型多级轴流压气机非设计工况进行了数值计算,分析了近喘振工况下的流场特性。结果表明:在近喘振点时气流流量减小,在叶片吸力面尾缘处容易出现分离,而且叶根附近分离最强。数值模拟结果与实验数据吻合较好,可为压气机的设计和优化提供参考。
In this paper, the internal flow of the multistage axial compressor was calculated based on Reynolds averaged N-S formulation and one formulation tubulence model at off-design points, using mixing plane method and PC network parallel computational technique. The performance of flow near choke points was analysised. Results show that mass flow rate decreases and flow separates at tailing edge of suction surface especially at blade root near the choke points. CFD results are good agree with experimental results, and can be used for design and optimization of compressor.
出处
《汽轮机技术》
北大核心
2010年第4期250-252,共3页
Turbine Technology
关键词
湍流模型
轴流压气机
数值计算
三维流场
tubulence model
axial compressor
numerical simulation
3D flow field
