| 摘要: |
| 为了探索机匣处理作用下转/静子的轴向匹配方法以进一步提高压气机级的失速裕度，研究了静子的叶型安装角及“弯”、“掠”规律对压气机性能的影响，针对机匣处理与优化静子的组合结构进行了非定常数值模拟，阐述了该结构的扩稳机理以及压气机新的失速机制。研究结果表明，在机匣处理作用下，静子成为压气机失速的触发因素，通过对静子叶型安装角及“弯”、“掠”规律的优化均可进一步提高压气机级的失速裕度，其中改变静子“弯”型对压气机级失速裕度的改善最大。组合应用机匣处理与尖部反弯根部正弯静子后，压气机效率基本不变，失速裕度提升了80.2%，较单独使用机匣处理提升30.9%。在该组合结构作用下，压气机的失速由静子触发，静子叶根吸力面在激波作用下发生附面层分离，且与轮毂表面附面层相互作用形成角区涡，接近失速边界时，静子叶根形成 “前缘溢流，尾缘反流”现象，造成静子通道的大范围堵塞，诱发压气机失速。压气机级的扩稳应充分考虑机匣处理的影响，对静子进行优化设计。 |
| 关键词: 轴流压气机 机匣处理 转/静子匹配 失速裕度 静子“弯掠” |
| DOI：10.13675/j.cnki. tjjs. 180473 |
| 分类号:V231.3 |
| 基金项目:国家自然科学基金 51879216 51006084;陕西省自然科学基金 2018JQ5152;国家自然科学基金重点项目 51339005国家自然科学基金（51879216；51006084）；陕西省自然科学基金（2018JQ5152）；国家自然科学基金重点项目 （51339005）。 |
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| Study of Axial Matching of Rotor/Stator for a High-LoadedAxial Flow Compressor with Casing Treatment |
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1.Faculty of Water Resources and Hydroelectric Engineering，Xi’an University of Technology,Xi’an 710048，China;2.School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China;3.Collaborative Innovation Center of Advanced Aero-Engine，Beijing 100191，China
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| Abstract: |
| In order to investigate the method of axial matching of rotor/stator on a high-loaded axial flow compressor with casing treatment for a further improvement of compressor stability， the effects on compressor performance of the installation angle and the laws of sweep and lean of stators were numerically studied. The flow mechanism of stability improvement was analyzed with the method of unsteady simulations for the combination of casing treatment and optimized stator, and the compressor’s stall mechanism was also studied. The results show that the stall of the compressor is triggered by the compressor stator. The compressor’s stability can be improved further by optimizing the installation angle or the sweep and lean laws of stators. The stability enhancement is maximized by optimizing the lean law of stators. The compressor’s stability is improved by 80.2% and the adiabatic efficiency remains unchanged by the combination of casing treatment and re-designed stator with positively curved blade tip and negatively curved blade root. The compressor stability is improved further by 30.9% compared with the case with only casing treatment. The compressor’s stall is triggered by the stator. The boundary layer of suction surface at stator’s root is separated under the effect of passage shock. It interacts with the boundary layer of hub surface resulting in a corner vortex. The flow phenomenon of “leading edge spillage, trailing edge backflow” is observed at the operating condition of near stall. The induced blockage in the stator triggers the compressor’s stall. The stator should be optimized for a compressor stage under the effect of casing treatment to achieve a better stability improvement. |
| Key words: Axial flow compressor Casing treatment Matching of rotor/stator Stall margin Sweep and lean of stator |
