CAJ | 학술논문

为了明确跨声速轴流压气机内部流场结构，数值模拟了NASA Rotor37转子，结合λ2准则分析流场参数，探索流动的规律和旋涡结构。研究发现，压气机转子的旋涡模型主要由马蹄涡、壁角涡、径向涡、脱落涡、泄漏涡、诱导涡和分离涡等7个旋涡组成。马蹄涡吸力面分支耗散，压力面分支向相邻的吸力面发展。壁角涡与脱落涡位于叶根角区，引起流动损失和角区失速。径向涡位于激波后吸力面的分离区内，它扩大吸力面分离、引起低能流体向叶顶堆积。激波与叶尖泄漏在叶顶通道中形成3涡：泄漏涡、诱导涡和分离涡，而叶栅通道出口存在分离涡和由泄漏涡与诱导涡合成的叶顶通道涡。泄漏涡与诱导涡破碎在流道中间产生的堵塞区，分离涡造成吸力面尾缘的低速区，共同触发跨声速压气机的失稳。
위료명학과성속축류압기궤내부류장결구，수치모의료NASA Rotor37전자，결합λ2준칙분석류장삼수，탐색류동적규률화선와결구。연구발현，압기궤전자적선와모형주요유마제와、벽각와、경향와、탈락와、설루와、유도와화분리와등7개선와조성。마제와흡력면분지모산，압력면분지향상린적흡력면발전。벽각와여탈락와위우협근각구，인기류동손실화각구실속。경향와위우격파후흡력면적분리구내，타확대흡력면분리、인기저능류체향협정퇴적。격파여협첨설루재협정통도중형성3와：설루와、유도와화분리와，이협책통도출구존재분리와화유설루와여유도와합성적협정통도와。설루와여유도와파쇄재류도중간산생적도새구，분리와조성흡력면미연적저속구，공동촉발과성속압기궤적실은。
To study the flow structure in transonic axial compressor,numerical simulation was conducted with NASA Rotor37 and the flow field parameters were analyzed to explore the vortex flow pattern and structure coupled with the λ2 criteria. It is found that vortex model in the rotor is consisted of seven major vortexes:horse?shoe vortex,corner vortex,shedding vortex,radial vortex,leakage vortex,induced vortex and separation vortex. Suction side leg of horseshoe vortex is dissipated while pressure side leg develops to adjacent suction side. Major effect of shedding vortex and corner vortex induces flow loss and hub corner stall,which are located at the root of blade. Radial vortex,which is located behind shock and in separation zone,enlarges the suction side separation and causes migration of low energy fluid in boundary layer to the tip. Coupling of shockwave and tip leakage in?duces the formation of three vortex structure in blade tip passage,namely leakage vortex,induced vortex and sepa?ration vortex. At outlet of tip cascade,there are two vortexes,separation vortex and tip passage vortex combined by leakage vortex and induced vortex. Blockage in the middle of the flow channel caused by the crushing of leak?age vortex and induced vortex,as well as the low-speed zone caused by separation vortex,trigger instability of transonic axial compressor.