涡桨发动机舱引射通风冷却数值研究  

Numerical Study on Exhaust Ejection and Nacelle Cooling of Turboprop Engine

作　　者：陈尧 单勇[1] 张靖周[1] CHEN Yao;SHAN Yong;ZHANG Jing-zhou(Nanjing University of Aeronautics and Astronautics,Nanjing 211000,China)

机构地区：[1]南京航空航天大学,江苏南京211000

出　　处：《航空计算技术》2024年第1期76-81,共6页Aeronautical Computing Technique

基　　金：国家科技重大专项资助(J2019-III-0009-0053)

摘　　要：以涡轮螺旋桨飞机的排气系统/短舱为研究对象,构建了机翼/机身/螺旋桨一体的发动机短舱仿真物理模型,采用多参考坐标系(MRF)法对螺旋桨滑流进行了模拟,并探究了不同排气管长度下发动机舱内的流动和换热情况。结果表明:在研究参数范围内,随排气管混合管段长度增加,在无滑流状态下,排气管中间环缝的引射流量上升18.3%,排气管末端环缝引射流量上升0.27 kg/s;在有滑流状态下,中间环缝引射流量保持在0.174 kg/s左右基本不变,末端环缝引射流量相对增加了35.8%,混合管段长度变化对末端环缝引射影响较大。排气管外管温度分布具有不对称性,滑流引入后,表面平均温度下降15 K,降幅4%;混合管段壁面温度受引射出口回流区和高温排气影响略有升高。A simulation physical model was constructed for the integrated engine nacelle of a turboprop aircraft,focusing on the exhaust system/short nacelle.The model incorporated the wing,fuselage,and propeller components.The slipstream of the propeller was simulated using the multiple reference frames(MRF)method,and the flow and heat transfer characteristics inside the engine nacelle were investigated for different exhaust pipe lengths.The results show that:within the scope of the parameters studied in this article.As the length of the mixing tube segment increases from 28 mm to 196 mm.Under the condition of no slipstream,the injection flow rate of the annular seam at the middle of exhaust nozzle increases by 18.3%,and the injection flow rate of the annular seam at the end of exhaust nozzle increases by 0.27 kg/s.Under the condition of slipstream,the injection flow rate of the middle annular seam remains around 0.174 kg/s,while the injection flow rate of the end annular seam increases by 35.8%.The change in length of the mixed pipe section has a significant impact on the injection of the end annular seam.The exhaust nozzle outer wall temperature distribution is asymmetric.The average temperature decreases by 15 K,4%.The mixing tube is slightly increased in wall temperature due to the influence of the outlet reflux zone and high temperature exhaust gas.

关 键 词：涡桨发动机 排气引射 通风冷却 螺旋桨滑流 多参考坐标系 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]