| 压气机叶栅紊流减阻试验研究 |
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| 引用本文： | 苗润田,王连贵,唐智明,高歌.压气机叶栅紊流减阻试验研究[J].航空动力学报,1991,6(1):13-16,89-90. |
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| 作者姓名： | 苗润田 王连贵 唐智明 高歌 |
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| 作者单位： | 沈阳黎明发动机制造公司(苗润田，王连贵
)，北京航空航天大学(唐智明，高歌) |
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| 摘 要： | 本文叙述压气机叶片表面刻花纹对叶栅性能的影响。实验表明 ,适当的花纹型式可使叶栅的临界马赫数 ,气流转折角以及最大静压比等主要性能指标均有明显提高。
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| 收稿时间： | 5/1/1990 12:00:00 AM |
EXPERIMENTAL INVESTIGATION OF TURBULENT DRAG REDUCTION IN COMPRESS CASCADE |
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| Miao Runtian,Wang Liangui,Gao Ge and Tang Zhiming.EXPERIMENTAL INVESTIGATION OF TURBULENT DRAG REDUCTION IN COMPRESS CASCADE[J].Journal of Aerospace Power,1991,6(1):13-16,89-90. |
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| Authors: | Miao Runtian Wang Liangui Gao Ge and Tang Zhiming |
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| Institution: | Shenyang Aeroengine Manufacture Company;Shenyang Aeroengine Manufacture Company;Beijing University of Aeronautics and Astronautics;Beijing University of Aeronautics and Astronautics |
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| Abstract: | Recent researches of theory and experiments indicate that turbulent drag is directly related to tiny coherent(organized)structure inside the turbulent boundary,and in turbulent flow field the flow drag of the specially designed non-smooth surface can be less than that of smooth surface.Based upon the above mentioned theory,six compressor cascades with different patterned surfaces have been experimented.The profile of the cascades was chosen from a stator vane of a reference compressor.The experiments have been performed in a near-sonic wind tunnel.The results obtained at the same Mach number as the reference compressor works indicate that the appropriate patterns on the surface improve the performances of cascades.Compared with the reference smooth cascade,the best one of six tested cascades raised the critical Mach number by 7 3 percent.The air flow deflection angle at the design conditions increased by 0 9°.Correspondingly,the deviation angle decreased by 0 9°.And maximum static compression ratio rised by 0 0177.The another one of the tested cascades obtained similar results.A brief analysis of the experimental results is also presented. |
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