TBCC发动机进气机匣流道评估与优化  

Evaluation and improvement of a TBCC engine inlet-case flow passage

作　　者：王俊[1] 余华蔚[1] 蔡留成[1] 杨伟[1] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500

出　　处：《燃气涡轮试验与研究》2015年第1期49-53,共5页Gas Turbine Experiment and Research

摘　　要：对涡轮基组合循环(TBCC)发动机进气机匣进行全三维流场计算,评估进气机匣流道的流场和性能,发现进气机匣流道中气流损失过大,总压恢复系数不满足指标要求,需进行优化。然后根据流场分析结果和流道截面积变化,使用三次样条插值方法对进气机匣流道进行优化,使流道截面积变化更为平缓。对修改设计后的流道再进行全三维流场计算分析,反复迭代使得最终的进气机匣流道和支板的总压恢复系数大幅提高,并满足指标要求。Firstly, the original flow-passage was computed by three-dimensional CFD software, and the flow field was analyzed. It could find that the airflow loss was too much in the original inlet-case flow pas？sage, and the total pressure recovery coefficient didn’t meet the design requirements, so the flow-passage should be improved. Then, the flow passage was optimized by the cubic spline method to make the cross sec？tion flatter. The optimized flow passage was computed by three-dimensional CFD software, and the flow field was analyzed. Finally, the optimized inlet-case was gained after several rounds of iteration, the total pressure recovery coefficient of the new flow passage and strut was higher and could meet the targets.

关 键 词：涡轮基组合循环发动机 进气机匣 三次样条 优化设计 三维计算 

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]