跨声速轴流压气机转子Rotor37周向槽机匣处理的数值研究
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摘要
以跨声速压气机转子Rotor37为研究对象,采用商业软件NUMECA数值研究了单槽处理机匣的轴向位置对于压气机性能及内部流场的影响。周向槽处理机匣的宽度为3 mm,深度为10倍叶尖间隙,即3.56 mm,起始位置分别位于轮缘机匣尖部型面的10%、20%、30%、40%、50%相对弦长处。数值计算结果表明:原始光壁压气机转子的失速原因为叶尖泄漏流动引发的低速区对于尖部叶片通道的堵塞,其稳定工作裕度为14.74%。采取的周向槽机匣处理能够改变转子叶尖流动堵塞状况。当机匣处理起始位置位于30%相对弦长时,压气机转子稳定工作裕度的提升量最大,相比原始压气机转子的稳定裕度提高了1.86%。
Based on the transonic compressor rotor,Rotor37,the effect of the axial position of single slot treated casing on the compressor's performance and internal flow-field are numerically investigated by commercial software NUMECA. The casing treatment is 3 mm in width and 10 times tip clearance in depth,which is 3. 56 mm. The start of these casing treatments are respectively located at the 10%,20%,30%,40% and 50% relative chord length of the tip blade section. Numerical investigations reveal that the flow blockage caused by tip leakage vortex is the main cause of stall in original compressor rotor and the calculated stall margin is 14. 74%. The circumferential groove casing treatment used can change the flow condition of tip region. The increasing of compressor rotor's stability margin is biggest when the start of casing treatment is located on 30% of relative chord length,which increases by 1. 86% than original compressor rotor.
Based on the transonic compressor rotor,Rotor37,the effect of the axial position of single slot treated casing on the compressor's performance and internal flow-field are numerically investigated by commercial software NUMECA. The casing treatment is 3 mm in width and 10 times tip clearance in depth,which is 3. 56 mm. The start of these casing treatments are respectively located at the 10%,20%,30%,40% and 50% relative chord length of the tip blade section. Numerical investigations reveal that the flow blockage caused by tip leakage vortex is the main cause of stall in original compressor rotor and the calculated stall margin is 14. 74%. The circumferential groove casing treatment used can change the flow condition of tip region. The increasing of compressor rotor's stability margin is biggest when the start of casing treatment is located on 30% of relative chord length,which increases by 1. 86% than original compressor rotor.
引文
1卢家玲.轴流压气机机匣处理及其机理研究.西安:西北工业大学,2007Lu Jialing.Study of axial compressor casing treatment and its mechanism.Xi'an:Northwestern Polytechnical University,2007
2 卢新根,楚武利,朱俊强,等.轴流压气机机匣处理研究进展及评述.力学进展,2006;36(2):222—232Lu Xingen,Chu Wuli,Zhu Junqiang,et al.Progress and review of axial compressor casing treatment.Advances in Mechanics,2006;36(2):222—232
3 朱俊强,刘志伟.4种不同型式机匣处理的实验研究及机理分析.航空学报,1997;18(5):567—570Zhu Junqiang,Liu Zhiwei.Four different type of experiment study and mechanism analysis of casing treatment.Acta Aeronautics ef Astronautics,1997;18(5):567—570
4 Azimian A R,Elder R L,Mckenzie A B.Application of recess vaned casing treatment to axial flow fans:ASME GT-89-68.New York:ASME,1989
5 黄旭东,陈海昕,符松,等.Rotor 37顶隙泄漏流的演化、影响及机匣处理.航空动力学报,2010;25(12):2673—2682Huang Xudong,Chen Haixin,Fu Song,et al.Development of the tip leakage flow in NASA rotor 37 and casing treatment.Journal of Aerospace Power,2010;25(12):2673—2682
6 张皓光,楚武利,吴艳辉,等.自适应流通机匣处理改善压气机性能的机理.推进技术,2010;31(3):301—308Zhang Haoguang,Chu Wuli,Wu Yanhui,et al.Flow mechanisms of improving compressor performance through self recirculation casing treatment.Journal of Propulsion Technology,2010;31(3):301—308
7 刘志伟,张长生.周向槽机匣处理增加失速裕度的改进机理.西北工业大学学报,1986;4(4):405—416Liu Zhiwei,Zhang Changsheng.The circumferential groove casing treatment increased the improvement mechanism of stall margin.Journal of Northwestern Polytechnical University,1986;4(4):405—416
8 邬扬杰.机匣处理对轴流压气机性能的影响.热能动力工程,1989;4(5):16—20Wu Yangjie.Casing treatment on the influence of axial flow compressor performance.Journal of Engineering for Thermal Energy and Power,1989;4(5):16—20
9 卢新根.轴流压气机内部流动失稳及其被动控制策略研究.西安:西北工业大学,2007Lu Xingen.Study on internal flow instability and passive control strategy of axial compressor.Xi'an:Northwestern Polytechnical University,2007
10 Takata H,Tsakada Y.Stall margin improvement by easing treatment—Its mechanism and effectiveness.ASME Journal of Engineering for Power,1977;99(3):121—133
11 谢芳.轴流压气机叶尖间隙影响失速的机理及周向单槽机匣处理扩稳研究.西安:西北工业大学,2015Xie Fang.Effect of tip clearance on stall and circumferential single grooves improving the stability on axial-flow compressors.Xi'an:Northwestern Polytechnical University,2015
2 卢新根,楚武利,朱俊强,等.轴流压气机机匣处理研究进展及评述.力学进展,2006;36(2):222—232Lu Xingen,Chu Wuli,Zhu Junqiang,et al.Progress and review of axial compressor casing treatment.Advances in Mechanics,2006;36(2):222—232
3 朱俊强,刘志伟.4种不同型式机匣处理的实验研究及机理分析.航空学报,1997;18(5):567—570Zhu Junqiang,Liu Zhiwei.Four different type of experiment study and mechanism analysis of casing treatment.Acta Aeronautics ef Astronautics,1997;18(5):567—570
4 Azimian A R,Elder R L,Mckenzie A B.Application of recess vaned casing treatment to axial flow fans:ASME GT-89-68.New York:ASME,1989
5 黄旭东,陈海昕,符松,等.Rotor 37顶隙泄漏流的演化、影响及机匣处理.航空动力学报,2010;25(12):2673—2682Huang Xudong,Chen Haixin,Fu Song,et al.Development of the tip leakage flow in NASA rotor 37 and casing treatment.Journal of Aerospace Power,2010;25(12):2673—2682
6 张皓光,楚武利,吴艳辉,等.自适应流通机匣处理改善压气机性能的机理.推进技术,2010;31(3):301—308Zhang Haoguang,Chu Wuli,Wu Yanhui,et al.Flow mechanisms of improving compressor performance through self recirculation casing treatment.Journal of Propulsion Technology,2010;31(3):301—308
7 刘志伟,张长生.周向槽机匣处理增加失速裕度的改进机理.西北工业大学学报,1986;4(4):405—416Liu Zhiwei,Zhang Changsheng.The circumferential groove casing treatment increased the improvement mechanism of stall margin.Journal of Northwestern Polytechnical University,1986;4(4):405—416
8 邬扬杰.机匣处理对轴流压气机性能的影响.热能动力工程,1989;4(5):16—20Wu Yangjie.Casing treatment on the influence of axial flow compressor performance.Journal of Engineering for Thermal Energy and Power,1989;4(5):16—20
9 卢新根.轴流压气机内部流动失稳及其被动控制策略研究.西安:西北工业大学,2007Lu Xingen.Study on internal flow instability and passive control strategy of axial compressor.Xi'an:Northwestern Polytechnical University,2007
10 Takata H,Tsakada Y.Stall margin improvement by easing treatment—Its mechanism and effectiveness.ASME Journal of Engineering for Power,1977;99(3):121—133
11 谢芳.轴流压气机叶尖间隙影响失速的机理及周向单槽机匣处理扩稳研究.西安:西北工业大学,2015Xie Fang.Effect of tip clearance on stall and circumferential single grooves improving the stability on axial-flow compressors.Xi'an:Northwestern Polytechnical University,2015