进、排气壳对全流道大膨胀比涡轮性能影响研究  

Effects of Inlet and Exhaust Casings on Performance of Turbine with Large Expansion Ratio of Full Flow

作　　者：柴家兴 马国骏 高杰[2] 岳国强[2] 郑群[2] CHAI Jia-xing;MA Guo-jun;GAO Jie;YUE Guo-qiang;ZHENG Qun(AECC Shenyang Engine Research Institute,Shenyang 110015,China;College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China)

机构地区：[1]中国航发沈阳发动机研究所,辽宁沈阳110015 [2]哈尔滨工程大学动力与能源工程学院,黑龙江哈尔滨150001

出　　处：《推进技术》2022年第1期364-374,共11页Journal of Propulsion Technology

基　　金：国家自然科学基金(51779051,51979052);航空动力基金(6141B09050392)。

摘　　要：为了分析船用增压器涡轮机进、排气系统对涡轮级性能的影响,采用数值模拟方法对全流道大膨胀比跨声速涡轮与进、排气壳耦合计算,探索进、排气壳耦合对涡轮级性能参数的影响,结果表明:进气壳主要影响静叶10%和50%叶高前缘的来流气流角周向分布,静叶排会减弱进气壳带来的参数周向不均匀性,排气壳主要影响动叶尾缘0°与180°周向位置总压与静压分布,进、排气壳耦合涡轮级总静效率比均匀边界涡轮级下降0.25%。In order to analyze the effects of marine turbocharger turbine inlet and exhaust systems on turbine performance,the numerical simulation method was used to calculate the full-flow large expansion ratio transonic turbine coupling the inlet and exhaust casings for the turbocharger turbine.And it explored the performance parameters of the turbine stage with inlet and exhaust casings.The results show that the inlet casing mainly affects circumferential distribution of airflow angle at 10%and 50%blade height leading edge of the stator.And the stator rows weaken the circumferential non-uniformity of the parameters brought by the inlet casing.The exhaust casing mainly affects the total pressure and static pressure distribution at the 0°and 180°circumferential positions of the trailing edge of the rotor.And total to static efficiency of the turbine coupled inlet and exhaust casings is re-duced by 0.25%compared to the uniform boundary turbine.

关 键 词：增压器涡轮机 全流道 大膨胀比 跨声速 进、排气壳耦合 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]