Method of calculating GTE gas-thermodynamic parameters with blade row description of an axial multistage compressor

Abstract


A method of calculating the operating performance of a turboshaft gas turbine engine for steady- state conditions has been developed based on a mathematical model with a row- after- row presentation of a multistage axial compressor. This method as opposed to the existing ones makes it possible to determine gas turbine engine gas-thermodynamic parameters at different ratings taking into account such factors as air bleeding and blow off directly from the air-gas channel, the variation of geometrical parameters of compressor blade rows and meridian bypasses and changes in the programme of regulating variable stator vanes. The results of investigating the thermodynamic parameters of the main units, their elements and performance characteristics of a turboshaft gas turbine engine are presented for a wide range of rotor speeds (throttle performance).  Comparisons between the computational results and the experimental data are made, their agreement is shown to be satisfactory.


About the authors

L. G. Boyko

National Aerospace University named after N. E. Zhukovsky "KhAI", Kharkov

Author for correspondence.
Email: boyko@d2.khai.edu

Ukraine

Doctor of Sciences (Engineering), Professor

Head of the Department of Aircraft Engine Theory

E. L. Karpenko

National Aerospace University named after N. E. Zhukovsky "KhAI", Kharkov

Email: boyko@d2.khai.edu

Ukraine

Candidate of Sciences (Engineering)

Senior Lecturer of the Department of Aircraft Engine Theory

U. F. Akhtemenko

SE Ivchenko-Progress, Zaporozhye

Email: ahktemenko@gmail.com

Ukraine

Leading Engineer

References

Statistics

Views

Abstract - 83

PDF (Russian) - 80

Article Metrics

Metrics Loading ...

PlumX

Dimensions

Refbacks

  • There are currently no refbacks.

Copyright (c) 2015 VESTNIK of the Samara State Aerospace University

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies