| Impact of Wake on Downstream Adjacent Rotor in Low-speed Axial Compressor |
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| 引用本文： | Xinqian ZHENG Sheng ZHOU School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing,China,100083. Impact of Wake on Downstream Adjacent Rotor in Low-speed Axial Compressor[J]. 热科学学报(英文版), 2004, 13(2): 114-120. DOI: 10.1007/s11630-004-0018-3 |
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| 作者姓名： | Xinqian ZHENG Sheng ZHOU School of Jet Propulsion Beijing University of Aeronautics and Astronautics Beijing China 100083 |
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| 作者单位： | Xinqian ZHENG Sheng ZHOU School of Jet Propulsion，Beijing University of Aeronautics and Astronautics，Beijing，China，100083 |
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| 摘 要： | This paper investigates the effect of upstream wake on unsteady separated flow field of downstream adjacent vanes by solving 2D unsteady Reynolds-averaged Navier-Stokes equations discretized by a high-order scheme. The results indicated that the maximum relative reduction of loss coefficient was 27.2% when the relative passing frequency (the ratio of wake passing frequency to the characteristic frequency of trailing-vortex shedding of downstream adjacent rotor) is less than 2.5. The amplitude of wake defect exists a threshold value and the aerodynamic performance is enhanced monotonically with the amplitude of wake defect basically. The effective range of incidence must be greater than 8°, which is near the stall boundary.
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Impact of wake on downstream adjacent rotor in low-speed axial compressor |
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| Xinqian Zheng,Sheng Zhou. Impact of wake on downstream adjacent rotor in low-speed axial compressor[J]. Journal of Thermal Science, 2004, 13(2): 114-120. DOI: 10.1007/s11630-004-0018-3 |
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| Authors: | Xinqian Zheng Sheng Zhou |
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| Affiliation: | (1) School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, 100083 Beijing, China |
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| Abstract: | This paper investigates the effect of upstream wake on unsteady separated flow field of downstream adjacent vanes by solving 2D unsteady Reynolds-averaged Navier-Stokes equations discretized by a high-order scheme. The results indicated that the maximum relative reduction of loss coefficient was 27.2% when the relative passing frequency (the ratio of wake passing frequency to the characteristic frequency of trailing-vortex shedding of downstream adjacent rotor) is less than 2.5. The amplitude of wake defect exists a threshold value and the aerodynamic performance is enhanced monotonically with the amplitude of wake defect basically. The effective range of incidence must be greater than 8°, which is near the stall boundary. |
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| Keywords: | unsteady flow separated flow rotor/stator interaction axial flow compressor. |
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