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Joint prediction of aircraft gas turbine engine axial flow compressor off-design performance and surge line based on the expanded method of generalized functions

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Abstract

The paper discusses the development of simulation software COMPRESSOR for preliminary design of gas turbine engines axial flow and centrifugal compressor and multistage axial compressor off-design performance prediction. The off-design performance prediction for individual axial compressor stages is based on the modified Ol’shtein method. The surge line prediction for axial compressors is based on incidence angle limitation and Howell’s method.

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Authors and Affiliations

  1. Ufa State Aviation Technical University, ul. K. Marksa 12, Ufa, the Republic of Bashkortostan, 450000, Russia

    A. B. Mikhailova, D. A. Akhmedzyanov, Yu. M. Akhmetov & A. E. Mikhailov

Authors
  1. A. B. Mikhailova
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  2. D. A. Akhmedzyanov
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  3. Yu. M. Akhmetov
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  4. A. E. Mikhailov
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Corresponding author

Correspondence to A. B. Mikhailova.

Additional information

Original Russian Text © A.B. Mikhailova, D.A. Akhmedzyznov, Yu.M. Akhmetov, A.E. Mikhailov, 2014, published in Izvestiya VUZ. Aviatsionnaya Tekhnika, 2014, No. 3, pp. 55–59.

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Mikhailova, A.B., Akhmedzyanov, D.A., Akhmetov, Y.M. et al. Joint prediction of aircraft gas turbine engine axial flow compressor off-design performance and surge line based on the expanded method of generalized functions. Russ. Aeronaut. 57, 291–296 (2014). https://doi.org/10.3103/S106879981403012X

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  • DOI: https://doi.org/10.3103/S106879981403012X

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