变几何涡轮与可调喷管发动机总体性能研究  

Study on general engine performance of variable geometry turbines and adjustable nozzle

作　　者：吴川 赵军[1] 陶睿 WU Chuan;ZHAO Jun;TAO Rui(College of Aviation Engineering,Civil Aviation Flight University of China,Guanghan 618307,China)

机构地区：[1]中国民用航空飞行学院航空工程学院,四川广汉618307

出　　处：《兵器装备工程学报》2023年第5期67-76,共10页Journal of Ordnance Equipment Engineering

基　　金：航空宇航科学与技术优势特色学科建设(D202105)。

摘　　要：为更加全面地展现变几何涡轮和可变喷管对发动机性能的影响情况,使用部件法对发动机进行建模,然后分别在改变高压涡轮第1级导向器喉道面积、改变低压涡轮第1级导向器喉道面积和改变喷管出口面积的情况下,系统地分析了发动机性能的变化情况,对总体性能参数进行了定量的研究。结果表明:增加高压涡轮流通能力或低压涡轮流通能力,尾喷管进口总温与总压均升高,推力和燃油消耗率均增加;当高压涡轮流通能力增加10%时,推力仅增加1.69%,燃油消耗率增加2.52%,而当低压涡轮流通能力增加10%时,推力增加13.16%,耗油率也增加12.42%;扩大尾喷管出口面积,尾喷管进口总温与总压均降低,推力和燃油消耗率均减小,当尾喷管出口面积增加10%时,推力有16.19%的大幅降低,燃油消耗率减小4.02%。In order to fully reveal the impact of variable geometry turbines and variable nozzle on engine performance,this paper establishes a component-level simulation to model an engine.Then,the changes of the engine performance are systematically analyzed,and the overall performance parameters are quantitatively studied under the circumstances of respectively changing the flow area of the first-stage guide vanes of the high-pressure turbine,changing the flow area of the first-stage guide vanes of the low-pressure turbine and changing the nozzle outlet area.The research results show that when the flow capacity of the high-pressure turbine or the low-pressure turbine increases,both the total temperature and the total pressure of the nozzle inlet rise,and both the thrust and the specific fuel consumption also increase.When the flow capacity of the high-pressure turbine increases by 10%,the thrust increases by only 1.69%and the specific fuel consumption increases by 2.52%;while the flow capacity of the low-pressure turbine increases by 10%,the thrust increases by 13.16%and the specific fuel consumption also increases by 12.42%.When the nozzle outlet area expands,both the total temperature and the total pressure of the nozzle inlet decrease,and both the thrust and the specific fuel consumption reduce.When the nozzle outlet area expands by 10%,there is a significant 16.19%reduction in the thrust and a 4.02%reduction in the specific fuel consumption.

关 键 词：变几何高压涡轮 变几何低压涡轮 变喷管面积 性能研究 燃气涡轮发动机 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]