| 摘要: |
| 为获取预冷器对高超声速进气道内流特性的影响机理和影响规律，设计了一种在扩张段加入台阶型预冷器的高超声速轴对称进气道，并利用混合网格建立了仿真模型，获得了Ma6.0来流条件下带预冷器进气道与原型进气道在节流状态的数值仿真结果。结果表明：引入预冷器后进气道临界耐反压能力略有下降，并且进气道下游背压在1.0≤pb/p0<150时出口性能参数明显下降；预冷器上游总是存在节流，上游节流程度由预冷器的堵塞和出口背压共同决定，当pb/p0≤20时，上游流场结构完全由预冷器的堵塞作用决定，当pb/p0>20时，由两者共同决定；进气道下游背压在20≤pb/p0<275时，预冷器为上游流场带来消极影响，而当背压在20≤pb/p0<200范围时，预冷器的引入能有效改善下游流场品质，通过上下游的耦合作用，出口性能参数在pb/p0≥150后与原型进气道趋于一致。当pb/p0≥275时，唇罩侧放气缝对激波串根部低能流的抽吸使得预冷器几乎不对上游产生影响。 |
| 关键词: 高超声速 预冷器 轴对称进气道 流场结构 数值仿真 |
| DOI：10.13675/j.cnki.tjjs.2203001 |
| 分类号:V211.48 |
| 基金项目:国家科技重大专项（J2019-II-0014-0035）；江苏省科协青年科技人才托举工程（TJ-2021-052）；中国航发四川燃气涡轮院委课题、基础性军工科研院所某国家财政支持项目（GJCZ-0015-19）；1912项目。 |
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| Effects of Precooler on Aerodynamic Performance of Hypersonic Axisymmetric Inlet at Design Condition |
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LI Chao1,2, ZHANG Yue1, TAN Hui-jun1, WANG Juan-juan1,3, XUE Hong-chao1, ZHANG Han-tian1
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1.College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China;2.Jinan Key Laboratory of Advanced Gas-Turbine，Jinan Institute of Advanced Gas-Turbine，Jinan 251401，China;3.Science and Technology on Altitude Simulation Laboratory，AECC Sichuan Gas Turbine Establishment， Mianyang 621000，China
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| Abstract: |
| In order to obtain the influence mechanism and law of the precooler on the internal flow characteristics of the hypersonic inlet， a hypersonic axisymmetric inlet with a stepped precooler is designed in the expansion section， and a simulation model was established by using a hybrid grid， further， the numerical simulation results of the inlet with precooler and the prototype inlet in the throttling states under the condition of Ma6.0 free flow are obtained. The results show that after the introduction of the precooler， the critical back pressure capability of the inlet decreases slightly. And when 1.0≤pb/p0<150， the performance parameters of the inlet outlet decrease significantly. There is always throttling at the upstream of the precooler， and the throttling state at the upstream is determined by the blockage of the precooler and the back pressure at the outlet. When pb/p0≤20， the upstream flow field structure is completely determined by the blockage of the precooler， and when pb/p0>20， it is determined by both. When 20≤pb/p0<275， the precooler has a negative effect on upstream flow field， and when 20≤pb/p0<200， the introduction of precooler can effectively improve the quality of downstream flow field. Through the coupling effect of upstream and downstream， the outlet performance parameters tend to be consistent with the prototype inlet when pb/p0≥150. When pb/p0≥275， the suction of the low energy flow at the root of the shock train by the bleeding slot on the side of the lip makes the precooler almost have no influence on the upstream. |
| Key words: Hypersonic Pre-cooler Axisymmetric inlet Flow field structure Numerical simulation |
