Volume 29 Issue 8
Aug.  2014
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Article Navigation >  Journal of Aerospace Power  > 2014  >  (8): 1838-1845
ZHONG Yong-jian, TENG Jin-fang, XU Xi, QIANG Xiao-qing, WU Ya-dong, OUYANG Hua. Prediction method of stall margin in axial-flow transonic compressor[J]. Journal of Aerospace Power, 2014, (8): 1838-1845. doi: 10.13224/j.cnki.jasp.2014.08.012
Citation: ZHONG Yong-jian, TENG Jin-fang, XU Xi, QIANG Xiao-qing, WU Ya-dong, OUYANG Hua. Prediction method of stall margin in axial-flow transonic compressor[J]. Journal of Aerospace Power, 2014, (8): 1838-1845. doi: 10.13224/j.cnki.jasp.2014.08.012
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Prediction method of stall margin in axial-flow transonic compressor

doi: 10.13224/j.cnki.jasp.2014.08.012

  • 1. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China;

  • 2. School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai 200240, China

  • Received Date: 2013-05-14
  • Publish Date: 2014-08-28
    Abstract
  • Performance of single stage axial-flow transonic compressor Stage 35 of design pressure ratio 1.82 and Stage 37 of design pressure ratio 2.05 at different rotation speeds was presented. Based on the HARIKA program, three models for respectively predicting cascade efficiency, deviation angle and head rise were improved. Two methods for predicting stall margin of axial-flow compressors were used. The first one was separation mass flow prediction method in HARIKA program. The second one was stalling static pressure rise coefficient prediction method proposed by Koch. Good agreement was achieved between the computation results and experiment data. The efficiency error of Stage 35 at design point decreases from 3.9% to 1.5%. The efficiency error of Stage 37 decreases from 3.1% to 1.9%. The minimum error of mass flow of stall margin predicted by two methods is 1.3% and 1.6% respectively. The result indicates that two methods used to predict stall margin are feasible.

     

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