| 跨声速弯掠动叶压气机非定常流场的数值研究(英文) |
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| 作者单位： | 哈尔滨工业大学能源科学与工程学院，哈尔滨工业大学能源科学与工程学院，哈尔滨工业大学能源科学与工程学院 黑龙江哈尔滨 150001，黑龙江哈尔滨 150001，黑龙江哈尔滨 150001 |
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| 基金项目： | 国家自然科学基金，Chinese Specialized Research Fund for the Doctoral Program of Higher Education，Development Program for Outstanding Young Teachers in Harbin Institute of Technology |
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| 摘 要： | The unsteady 3D flow fields in a single-stage transonic compressor under designed conditions are simulated numerically to investigate the effects of the curved rotors on the stage performance and the aerodynamic interaction between the blade rows. The results show that, compared to the compressor with unurved rotors, the compressor under scrutiny acquires remarkable increases in efficiency with significantly reduced amplitudes of the time-dependent fluctuation. The amplitude of the pressure fluctuation around the stator leading edge decreases at both endwalls, but increases at the mid-span in the curved rotors. The pressure fluctuation near the stator leading edge, therefore, becomes more uniform in the radial direction of this compressor. Except for the leading edge area, the pressure fluctuatinn amplitude declines remarkably in the tip region of stator surface downstream of the curved rotor, but hardly changes in the middle and at the hub.
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| 关 键 词： | 跨音速压气机 不稳定流场 曲线转子 空气动力学交互作用 |
| 收稿时间： | 6 June 2007 |
Numerical Investigation of the Unsteady Flow in a Transonic Compressor with Curved Rotors |
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| Authors: | Mao Mingming Song Yanping Wang Zhongqi |
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| Institution: | School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China |
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| Abstract: | The unsteady 3D flow fields in a single-stage transonic compressor under designed conditions are simulated numerically to inves- tigate the effects of the curved rotors on the stage performance and the aerodynamic interaction between the blade rows. The results show that, compared to the compressor with un-curved rotors, the compressor under scrutiny acquires remarkable increases in efficiency with significantly reduced amplitudes of the time-dependent fluctuation. The amplitude of the pressure fluctuation around the stator leading edge decreases at both endwalls, but increases at the mid-span in the curved rotors. The pressure fluctuation near the stator lead- ing edge, therefore, becomes more uniform in the radial direction of this compressor. Except for the leading edge area, the pressure fluc- tuation amplitude declines remarkably in the tip region of stator surface downstream of the curved rotor, but hardly changes in the mid- dle and at the hub. |
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| Keywords: | transonic compressor unsteady flow field curved rotor aerodynamic interaction |
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