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Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method

Abbasi S., Pirnia A., Taghavi-Zenouz R.

Journal of Theoretical and Applied Mechanics

2018

Vol. 56 nr 4

1005--1015

In this paper, the effects of inlet flow distortion on performance maps and details of the flow field are investigated using the Streamline Curvature Method. The results are presented for both design and off-design conditions and compared with experimental data, which shows good agreement. The effects of inlet flow distortion are investigated by inlet total pressure variation in three different cases in the way that the average total pressure remains constant and equal to the design value. The results show that a relative increase in the total pressure at tip causes an increase in the pressure ratio and efficiency as well as a better performance in the choking region. Alternatively, a relative increase in the total pressure in hub causes opposite behavior and a better performance at the surging region.

The off-design performance prediction of axial compressor based on a 2D approach

Zhu X. C., Hu J. F., Ou-Yang H., Tian J., Qiang X. Q., Du Z. H.

Journal of Theoretical and Applied Mechanics

2013

Vol. 51 nr 3

523--531

The two-dimensional compressor flow simulation approach has always been a very valuable tool in compressor preliminary design studies, as well as performance predictions. In this context, a general development of the streamline curvature (SLC) method is elucidated firstly. Then a numerical method based on SLC is developed to simulate the internal flow of the compressor according to the development analysis and conclusion. Two certain transonic axial compressors are calculated by this 2D method. The speed lines and span-wise aerodynamic parameters are compared with the experiment data in order to demonstrate the method presented in this paper.