Obtaining an equation for computing profile losses in a blade row of axial turbine while design calculation

Аuthors

Baturin O. V.^*, Kolmakova D. A.^**, Popov G. M.^***, Matveev V. N.^****

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia

*e-mail: oleg.v.baturin@gmail.com
**e-mail: kolmakova.daria@gmail.com
***e-mail: popov@ssau.ru
****e-mail: valeriym2008@rambler.ru

Abstract

The article proposes a method for reliability evaluation of losses models based on statistical analysis of deviation of experimental data from calculated. It showed that those deviations are subjected to the normal distribution law, and could be described by the value of mathematical expectation  and mean-square deviation .

The values of profile losses were calculated by five well-known models for 170 various axial turbines cascades, representing the diversity of turbines employed in aircraft gas turbine engines. The findings were being compared with the experimental data. The results of comparison were subjected to statistical analysis. It was found, that the best model describing the profile losses in axial turbines was the model developed in the Central Institute of Aviation Motors (Russia). It allows calculate the profile losses deviating from the actual values of losses by 8 ± 84% with a probability of 95%.

With account for the above mentioned statistical criteria, a new equation was proposed based on the analysis of the profile losses’ nature and employing mathematical optimization techniques. This equation opens the possibility of defining the profile losses of an axial turbine more accurately than by the use of the studied models. It allows calculate the profile loss values in the axial turbine deviating from the actual values of losses by 10±61% with a probability of 95%. This new proposed equation accounts for more geometric and operational factors affecting the losses value.

Keywords:

axial turbine, profile losses, mathematical statistics, model

References

1. Wei N. Significance of Loss Models in Aerothermodynamics Simulation for Axial Turbines. Doctoral Thesis, 2000, KTH ISBN 91-7170-540-6, available at: http://citeseerx.ist.psu.edu/viewdoc/download?doi=10.1.1.12.5487&rep=rep1&type=pdf

2. Dahlquist A.N. Investigation of Losses Prediction Methods in 1D for Axial Gas Turbines. Thesis for the Degree of Master of Science Division of Thermal Power Engineering, Lund Institute of Technology Lund University, Sweden, 2008, available at: https://lup.lub.lu.se/luur/download?func=downloadFile&recordOId=1423748&fileOId=1423797

3. Horlock J.H. Axial Flow Turbines, Butterworths, UK, 1965, 268 p.

4. Ainley D.G., Mathieson G.C.R. An Examination of the Flow and Pressure Losses in Blade Rows of Axial-Flow Turbines. Reports & memoranda, no. 2891, British ARC, 1955, available at: http://www.aerade.aero/reports/arc/rm/2891.pdf

5. Dunham J., Came P.M. Improvements to the Ainley / Mathieson Method of Turbine Performance Prediction, ASME Journal of Engineering for Power, 1970, vol. 92, no. 3, pp. 252 – 256.

6. Venediktov V.D., Granovskii A.V. Atlas eksperimental’nykh kharakteristik ploskikh reshetok okhlazhdaemykh gazovykh turbin (Atlas of Experimental Characteristics of Cooled Gas Turbine Blade Cascades), Moscow, TsIAM, 1990, 393 p.

7. Lanshin A.I. Aviatsionnye dvigateli i silovye ustanovki (Aircraft engines and power plants), Moscow, TsIAM im. P. I. Baranova, 2010, 536 p.

8. Kacker S.C., Okapuu U. A Mean Line Prediction Method for Axial Flow Turbine Efficiency, ASME Journal of Engineering for Power, 1982, vol. 104, no. 2, pp. 111 – 119.

9. Abiants V.Kh. Teoriya gazovykh turbin reaktivnykh dvigatelei (Theory of the gas turbine jet engines). Moscow, Mashinostroenie, 1979, 246 p.

10. Belousov A.N., Musatkin N.F., Rad’ko V.M. Teoriya i raschet aviatsionnykh lopatochnykh mashin (Theory and calculation of aircraft turbomachinery), Samara, Izd-vo Samarskogo gosudarstvennogo aerokosmicheskogo universiteta, 2003, 344 p.

11. Denton J.D. Loss Mechanisms in Turbomachines, Journal of Turbomachinery, 1993, vol. 115, no. 4, pp. 621 – 656.

12. Lewis R.I. Turbomachinery performance analysis, Elsevier Science & Technology Books, 1996, 329 p.

13. Gusarov S.A. Elektronnyi zhurnal «Trudy MAI», 2012, no 53, available at: http://trudymai.ru/eng/published.php?ID=29397

14. Sigma Tekhnologiya. Programmnyi kompleks IOSO NM, available at: http://www.iosotech.com/ru/ioso_nm.htm

15. Egorov I.N., Kretinin G.V., Leshchenko I.A., S.V Kuptzov. IOSO Optimisation Toolkit – Novel Software to Create Better Design, 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimisation, 04 – 06 Sep. 2002, Atlanta, Georgia, doi.org/10.2514/6.2002-5514

16. Dennis B.H., Egorov I.N., Sobieczky H., Dulikravich G.S., Yoshimura S. Parallel Thermoelasticity Optimization of 3-D Serpentine Cooling Passages in Turbine Blades, ASME Turbo Expo 2003. Turbine Technical Conference and Exposition, June 16–19, 2003, Atlanta, Georgia, USA, ASME Paper No. GT2003-38180.

17. Komarov O.V. Sedunin V.A., Blinov V.L. Application of Optimisation Techniques for New High-Turning Axial Compressor Profile Topology Design, ASME Turbo Expo 2014. Turbine Technical Conference and Exposition, June 16–20, 2014, Düsseldorf, Germany, ASME Paper No. GT2014-25379.

18. Baturin, O.V., Popov G.M., Gorachkin E.S., Smirnova Y.D. Trudy MAI, 2015, no. 82, available at: http://trudymai.ru/eng/published.php?ID=58712

19. Marchukov E.Yu., Egorov I.N. Gas Dynamic Modernization of Axial Uncooled Turbine by Means of CFD and Optimization Software, IOP Conference Series: Materials Science and Engineering, 28–30 September 2017, Samara, Russia, vol. 302 (1), article number 012027.

20. Marchukov E.Yu., Egorov I.N., Popov G.M., Baturin O.V., Goriachkin E.S., Novikova Y.D., Kolmakova D.A. Gas Improving of the working process of axial compressors of gas turbine engines by using an optimization method, IOP Conference Series: Materials Science and Engineering, 28–30 September 2017, Samara, Russia, vol. 232 (1), article number 012041.

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