摘要
为了探究部件参数不确定性对发动机性能评估的影响,以涡扇发动机为研究对象,采用部件级建模方法建立航空发动机数值计算模型。通过拉丁超立方抽样不确定量化方法开展各部件参数以及耦合情况下部件参数不确定性对发动机性能参数的影响研究。结果表明:低压压气机效率参数不确定性造成推力和耗油率均值偏离起飞状态设计性能的程度最大,使推力均值平均增加0.54%,而耗油率均值平均减小0.40%。高压压气机效率参数不确定性造成推力和耗油率均值偏离起飞状态设计性能的程度最小;高压压气机效率和高压涡轮效率对推力和耗油率置信区间影响最大,使推力和耗油率的置信度范围平均增加0.74%和0.54%。低压压气机流量对推力和耗油率置信区间影响最小。通过对发动机各部件参数的不确定性分析可以辅助外场人员合理评估和判断发动机性能的变化情况。
In order to investigate the influence of component parameter uncertainty on engine performance evaluation,a numerical model for turbofan engines was established by using component-level modeling methods.The influence of component parameter uncertainties,as well as their coupled effects,on engine performance parameters was numerically investigated using the Latin hypercube sampling uncertainty quantification method.The results show that the uncertainty of the low-pressure compressor efficiency causes the mean values of thrust and specific fuel consumption to deviate from the takeoff-state design performance to the greatest extent,resulting in an average increase of 0.54%in the mean value of thrust and an average decrease of 0.40% in the mean value of specific fuel consumption.The uncertainty of high-pressure compressor efficiency caused the mean thrust and specific fuel consumption to deviate from the takeoff-state design performance to the smallest extent;the high-pressure compressor efficiency and high-pressure turbine efficiency have the greatest influence on the confidence intervals of thrust and specific fuel consumption,increasing the confidence intervals of thrust and specific fuel consumption by an average of 0.74% and 0.54%,respectively.The low-pressure compressor flow has the least effect on the confidence intervals of thrust and specific fuel consumption.Through uncertainty analysis of engine component parameters,field personnel can reasonably evaluate and judge the change of engine performance.
作者
林武军
于锦禄
尉洋
唐晓锟
LIN Wu-jun;YU Jin-lu;YU Yang;TANG Xiao-kun(Aviation Engineering School,Air Force Engineering University,Xi'an 710038,China;Unit 95926 of the Chinese People′s Liberation Army,Changchun 130000,China)
出处
《航空发动机》
北大核心
2025年第2期68-74,共7页
Aeroengine
基金
国家级研究项目(J2022-I-0003)资助。
