# INVESTIGATION OF INTERFERENCE INFLUENCE OF BLADE ROWS ON LOSSES IN AXIAL COMPRESSOR STAGE

## Authors

• Yuriy M. Tereshchenko National Aviation University
• Ekaterina Doroshenko National Aviation University
• Yuriy Yu. Tereshchenko National Aviation University
• Pavel Gumenyuk National Aviation University

## Keywords:

blade row, boundary layer, flow modeling, guide vanes, secondary losses, total pressure losses

## Abstract

Purpose: the purpose of this work is to investigate the total pressure losses in the input guide vanes, in the rotor wheel and the guide vanes of the axial compressor stage taking into account their gas-dynamic interference. Methods: the study was carried out by numerical simulation of three-dimensional flow in the stage of an axial compressor. An unstructured adaptive computational grid is constructed. The gas dynamic calculation of the flow in the stage of the axial compressor is performed using the Navier-Stokes system of equations, which was closed by the SST turbulent model. Results: a series of gas-dynamic flow calculations was performed at different values of the axial velocity at the inlet to the compressor stage. The circuit velocity at the peripheral radius in the calculated mode was u= 238.64 m/s. The coefficient of velocity at the entrance to the stage varied in the range =0.35…0.7. Based on the calculation results, the dependences of the total pressure loss coefficients from the input velocity coefficient for various elements of the stage of the axial compressor were constructed. Analysis of the results of the study shows that the greatest contribution to the overall balance of total pressure losses is made by losses in the guide vanes. Discussion: losses in the guide vanes increase due to the gas-dynamic interference of the rotor wheel and the guide vanes. The mutual influence of the blade rows of the rotor wheel and the guide vanes leads to a significant transformation of the velocities and pressures in the interblade channels. As a consequence, there is a redistribution of losses caused by circumferential and radial flow irregularity, end-flow and centrifugal forces. It can be expected that a reduction in the level of losses in the step of the axial compressor can be achieved by influencing the boundary layer in the end clearance of the rotor wheel.

## Author Biographies

### Yuriy M. Tereshchenko, National Aviation University

Doctor of Engineering. Professor.

Aeroengines Department, National Aviation University, Kyiv, Ukraine.

Education: Kiev Military Aviation Engineering Academy, Kyiv, Ukraine (1962)

Research area: aerodynamics of compressors.

### Ekaterina Doroshenko, National Aviation University

PhD.

Aeroengines Department, National Aviation University, Kyiv, Ukraine.

Education: National Aviation University, Kyiv, Ukraine (2008).

Research area: aerodynamics of compressors.

### Yuriy Yu. Tereshchenko, National Aviation University

PhD.

Aeroengines Department, National Aviation University, Kyiv, Ukraine.

Education: National Aviation University, Kyiv, Ukraine (2010).

Research area: aerodynamics of compressors.

### Pavel Gumenyuk, National Aviation University

Student.

Aeroengines Department, National Aviation University, Kyiv, Ukraine.

Education: National Aviation University, Kyiv, Ukraine.

Research area: aerodynamics of compressors.

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13-03-2018

## How to Cite

Tereshchenko, Y. M., Doroshenko, E., Tereshchenko, Y. Y., & Gumenyuk, P. (2018). INVESTIGATION OF INTERFERENCE INFLUENCE OF BLADE ROWS ON LOSSES IN AXIAL COMPRESSOR STAGE. Proceedings of National Aviation University, 74(1), 84–90. https://doi.org/10.18372/2306-1472.74.12295

## Section

MODERN AVIATION AND SPACE TEHNOLOGY