摘要
归纳和整理了现有环形扩压器性能分析模型,并将模型预测结果与若干种环形扩压器性能实验数据进行了比较,结果表明模型预测结果与对应实验数据一致性还是比较好的。在此基础上,应用所发展模型对某大涵道比涡扇发动机高/低压涡轮过渡流道环形扩压器进行了优化设计,最终获得的过渡流道环形扩压器性能指标与拟达到的性能指标比较符合,进一步表明了所给模型作为初步的涡轮机中环形扩压器设计设计与性能分析模型是可行的。
A method for predicting the performance of annular diffusers in turbomachinery is presented. The method is based on the model of onedimensional flow. The predictions from this model are in better agreement with available experimental data for a variety of annular diffuser geometries In addition a computer program has been developed, allowing this model technique to be readily applied to the design of intermediate turbine duct （ITD） in high bypassratio turbofan engines. It has been found that good performance objects of ITD may be obtained.
出处
《航空计算技术》
2013年第2期41-43,47,共4页
Aeronautical Computing Technique
基金
国家自然基金项目资助(51076131)
关键词
环形扩压器
压力恢复系数
总压损失系数
涡轮过渡流道
annular diffuser
pressure recovery coefficient
total pressure loss coefficient
intermediate turbine duct
