某型加力涡扇发动机特性的三层迭代模拟  

Simulation of the performances of an augmented turbofan engine using three-layer iterations

作　　者：吴虎[1] 廉小纯[1] 

机构地区：[1]西北工业大学航空动力与热力工程系,陕西西安710072

出　　处：《推进技术》2002年第2期118-120,共3页Journal of Propulsion Technology

基　　金：航空科学基金资助项目 ( 98C5 3 0 2 3 )

摘　　要：基于发动机各部件特性 ,应用总体匹配技术发展了混排涡扇发动机特性的数值模型 ,并针对某型涡扇发动机建立了相应的三层迭代模拟方法及相应的计算机程序。给出了该发动机在某一组合调节方案下的特性模拟结果。A model for simulating the performance of mixed-flow turbofan engines was presented based on the component characteristics of the engines. Numerical method was obtained using three-layer iterations, and the computer program to fulfil this was developed. An example for predicting the performance of an augmented turbofan engine was given. Comparisons between numerical results and experimental data showed good agreements. It was remarkable that proposed method was robust, and was computationally fast. It is apparent that this method is readily adaptable for analyzing full fight-envelope operation and combined control modes of coming generation military engines.

关 键 词：动力涡轮风扇发动机 可调截面喷管 迭代模拟 航空发动机 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]