上下游边界耦合对燃烧室流场的影响研究  

Research on the influence of upstream and downstream boundary coupling on flow field of the combustor

作　　者：张华军 邢力 黎武 徐华胜 李银怀 郑明新 梁勇 ZHANG Hua-jun;XING Li;LI Wu;XU Hua-sheng;LI Yin-huai;ZHENG Ming-xin;LIANG Yong(Military Representative Office of Chengdu Bureau of Air Force Equipment Department,Chengdu 610500,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]空装成都局某军事代表室,成都610500 [2]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2022年第4期13-19,共7页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(91841302)。

摘　　要：通过仿真解耦研究了燃烧室上下游边界对燃烧室流场的影响,并与试验结果进行了对比验证。结果表明,相比于单燃烧室仿真,基于多部件的联合变维仿真可以提高燃烧室内各部分压降的预测精度,能够更加真实地模拟出火焰筒内流场分布以及出口温度分布,且与试验值吻合更好;单燃烧室仿真相比燃烧室与高压涡轮导叶联算,火焰筒出口附近流线方向会偏高,进而影响径向温度分布趋势。单燃烧室仿真相比燃烧室与压气机末级导叶联算,会影响对二股流漩涡的预测精度,且不均匀的压气机出口流场,通过影响旋流器进气均匀性来影响燃烧的反应进程。相比单燃烧室仿真,基于多部件联合变维仿真的燃烧室温度分布系数和径向温度分布系数,在70%流道高度处的温度相对偏差最小(为-0.6%),其他高度处的温度相对偏差也相对较小,预测精度有较大的提升。The influence of the upstream and downstream boundary of the combustor on the flow field of the combustor is studied by simulation and decoupling. Compared with single-combustor simulation,variable dimension simulation based on multiple components can improve the prediction precision of pressure drop in each part of the combustor, and can simulate the distribution of flow field in combustor liner and outlet temperature more accurately. The results of the variable dimension simulation are in better agreement with experimental data. The flaw of single-combustor simulation by contrast with taking both combustor and HPT guide vane into consideration is thatthe streamline direction near the liner outlet is higher, therefore the radial temperature distribution trend is disturbed. Another disadvantage of singlecombustor simulation comes up when comparing it with joint calculation of combustor and final stage guide vane of compressor. Thefirst method affects prediction precision of the second stream vortex and the uneven flow field of compressor outlet influences the reaction process of combustion by influencing the inlet uniformity of the swirler. Compared with single-combustor simulation the temperature distribution coefficient and the radial temperature distribution coefficient of the combustor based on variable dimension simulation reach minimum temperature deviation(-0.6%) at 70% height of flow channel.Temperature deviation at other heights is also relatively small and the precision is greatly improved.

关 键 词：燃烧室 边界耦合 压气机导叶 高压涡轮导叶 航空发动机 

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]