Aeroacoustic characteristics of the axial compressor stage with tandem impeller

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Authors:

Е.V.Doroshenko, Cand. Sc. (Tech.), orcid.org/0000-0001-6495-3263, National Aviation University, Kyiv, Ukraine, e-mail: This email address is being protected from spambots. You need JavaScript enabled to view it.

Yu.M.Tereshchenko, Dr. Sc. (Tech.), Prof., orcid.org/0000-0003-4367-3232, National Aviation University, Kyiv, Ukraine, e-mail: This email address is being protected from spambots. You need JavaScript enabled to view it.

Yu.Yu.Tereshchenko, Cand. Sc. (Tech.), orcid.org/0000-0002-1908-0923, National Aviation University, Kyiv, Ukraine, e-mail: This email address is being protected from spambots. You need JavaScript enabled to view it.

А.O.Kushchinskiy, orcid.org/0000-0002-0175-8767, National Aviation University, Kyiv, Ukraine, e-mail: This email address is being protected from spambots. You need JavaScript enabled to view it.

Abstract:

Purpose. Comparative evaluation of aeroacoustic characteristics of the axial compressor stages with a single and equivalent tandem impeller.

Methodology. The research was performed using the numerical experiment. The flow parameters in the stage of the axial compressor were calculated by solving the non-stationary system of Navier – Stokes equations. The equations were closed by the model of turbulent viscosity SST. The stage of the compressor consisted of inlet guide vanes, the impeller and the guide vanes. The impeller of the modified axial compressor stage is designed as an equivalent tandem row. Acoustic sources of the axial compressor stage were calculated using the Ffowcs Williams – Hawkings equation.

Findings. The results of a comparative evaluation of the aeroacoustic characteristics of the axial compressor stages with a single and equivalent double-row impeller are obtained. The use of a tandem row instead of an equivalent single row in the impeller of the axial compressor stage makes it possible to increase the pressure ratio by 1‒15 %. In the design mode, the pressure ratio is increased by 8.5 %. A stage with a tandem impeller has greater acoustic efficiency than a compressor stage with a single impeller. The obtained results demonstrate a significant decrease in the acoustic pressure of the dipole source. In the design mode, the acoustic pressure of the dipole source decreases by more than 70 %, the acoustic pressure of the quadrupole source decreases by more than 10 %.

Originality. For the first time the results of a comprehensive study of the aerodynamic and acoustic characteristics of the axial compressor stage were obtained. The results allow estimating the efficiency of application of tandem row in the impeller of the low loaded subsonic stage of the axial compressor.

Practical value. The received recommendations can be used while designing impeller machines with a low level of acoustic emission.

References.

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4. Eshraghi, H. A., Boroomand, M. and Tousi, A. M., 2016. Developed Methodology in Design of Highly Loaded Tandem Axial Flow Compressor Stage. Journal of Applied Fluid Mechanics, 9(1), pp. 83‒94.

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6. Zhang, X., 2012. Aircraft noise and its nearfield propagation computations. Acta Mechanica Sinica, 28(4), pp. 960–977. DOI: 10.1007/s10409-012-0136-1.

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8. Hellmich, B. and Seume, J. R., 2008. Causes of acoustic resonance in a high-speed axial compressor. Journal of Turbomachinery, 130(3), pp. 031003-1–031003-9. DOI: 10.1115/1.2775487.

9. Laborderie, J., Soulat, L. and Moreau, S., 2014. Prediction of noise sourses in axial compressor from URANS simulation. Journal of Propultion and Power, 30(5), pp. 1257–1271. DOI: 10.2514/1.B35000.

10. Tereshchenko, Y., Doroshenko, E., Lastivka, I. and Tereshchenko, Y., 2017. Numerical study of flow in the stage of an axial compressor with different topology of computational grid. Eastern-European Journal of Enterprise Technologies, 3(7–87), pp. 28–33. DOI: 10.15587/1729-4061.2017.101315.

11. Tereshchenko, Y. M., Doroshenko, E. V. and Abolhasssan zade, J., 2015. Influence research of profile chords ratio on aerodynamic characteristics of tandem compressor cascade. Eastern-European Journal of Enterprise Technologies, 5/8(77), pp. 9–13. DOI: 10.15587/1729-4061.2015.50535.

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ISSN (print) 2071-2227,
ISSN (online) 2223-2362.
Journal was registered by Ministry of Justice of Ukraine.
Registration number КВ No.17742-6592PR dated April 27, 2011.

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