一种适用于压气机非定常流动的相位滞后算法

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Study of phase-lag algorithm for unsteady flow of compressor

National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University ofAeronautics and Astronautics, Beijing 100083, China

摘要: 应用相位滞后边界条件,以1∶1的转、静叶计算域,在不改变转子尾迹及静子势干扰的频率的条件下,计算叶轮机非定常流场.以NASAstage₆₇为算例,计算结果与实验数据相吻合,表明采用的方法具有较大的工程实用性.
- 航空、航天推进系统 /
- 压气机 /
- 非定常 /
- Navier-Stokes方程 /
- 相位滞后 /
- 并行
Abstract: Phase-lag boundary conditions were applied in unsteady flow calculation of turbomachinery by not changing the real frequency of rotor wake and potential disturbance of stator,with a 1∶1 ratio of rotor/stator.Based on the computations over NASA Stage67,the results were found to match the experimental data,showing that the method is suitable for engineering applications.
- aerospace propulsion system /
- compressor /
- unsteady /
- Navier-Stokes equations /
- phase-lag /
- parallel

[1]	Chen J P,Barter J W.Comparison of time-accurate calculations for the unsteady interaction in turbo machinery stage[R].AIAA-98-3292,July,1998.
[2]	Chen J P,Celestina M L,Adamczyk J J.A new procedure for simulating unsteady flows through turbo machinery blade passage[R].ASME-94-GT-151,June,1994.
[3]	Chen J P,Briley W R.A parallel flow solver for unsteady multiple blade row turbo machinery simulation[R].ASME-2001-GT-0348,June,2001.
[4]	莫则尧,袁国兴.消息传递并行编程环境[M].北京:科学出版社,2001.

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