| 跨声速串列转子失速机制的数值研究 |
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| 引用本文： | 宋明哲,袁巍,李绍斌. 跨声速串列转子失速机制的数值研究[J]. 航空动力学报, 2016, 31(1): 124-135. DOI: 10.13224/j.cnki.jasp.2016.01.017 |
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| 作者姓名： | 宋明哲 袁巍 李绍斌 |
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| 作者单位： | 1. 北京航空航天大学 能源与动力工程学院航空发动机气动热力国家级重点实验室, 北京 100191; |
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| 基金项目： | 国家自然基金(51106003) |
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| 摘 要： | 为了解决跨声速串列转子的低裕度问题,就必须了解跨声速串列转子的流场结构与失速机制.设计了叶尖切线速度为450m/s,负荷系数为0.56的高负荷跨声速串列转子.基于数值模拟的结果,分析了该串列转子在0.5mm叶尖间隙下的叶尖流场结构与失速机制,并在此基础上分别探讨了叶尖间隙和前、后排叶片周向位置对串列转子特性的影响和失速机制的变化.结果表明:前排叶片的叶尖区域是 影响串列转子稳定性的关键;随着叶尖间隙的增加,串列转子的失速机制也发生变化,从前排叶片叶尖区域的尾迹与径向潜流堵塞后排叶片通道转变为前排叶片叶尖泄漏流堵塞;在较大周向相对位置(后排叶片压力面周向远离前排吸力面)的情况下,串列转子获得最好的效果,随着周向相对位置(PP)的增加,失速部位从后排叶片转移至前排叶片.
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| 关 键 词： | 跨声速串列转子 失速机制 叶尖流场 叶尖间隙 周向相对位置 |
| 收稿时间： | 2014-05-19 |
Numerical investigation of stall mechanism for transonic tandem rotor |
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| SONG Ming-zhe,YUAN Wei and LI Shao-bin. Numerical investigation of stall mechanism for transonic tandem rotor[J]. Journal of Aerospace Power, 2016, 31(1): 124-135. DOI: 10.13224/j.cnki.jasp.2016.01.017 |
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| Authors: | SONG Ming-zhe YUAN Wei LI Shao-bin |
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| Affiliation: | 1. National Key Laboratory of Science and Technology on Aero-Engines Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China |
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| Abstract: | In order to enhance the stall margin of transonic tandem rotor, a better understanding about its flow structure and stall mechanism is required. Thus, a high-loaded transonic tandem rotor was designed to perform a loading coefficient of 0.56 at tip tangent speed of 450m/s. Based on the simulation results, firstly, the tip flow field and stall mechanism of this tandem rotor with the shroud gap of 0.5mm was analyzed, and then the influence of different tip clearances and percent pitch values on stall mechanism was studied. It is indicated that the tip area of forward blade plays a prominent role in the stability of transonic tandem rotor. Along with the increase of tip clearance, the stall mechanism of tandem rotor also changes from the stagnation of aft blade tip area caused by wake and subsurface flow to the blocking of forward blade tip area caused by the tip leakage flow. The tandem rotor will achieve its best effect under high percent pitch(PP) value, and the stall onset position will move from the aft blade towards the forward blade with the increase of percent pitch. |
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| Keywords: | transonic tandem rotor stall mechanism tip flow field tip clearance percent pitch |
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