An investigation of five models used to assess the profile losses in axial turbine cascades appears in this article: Soderberg model, Ainley&Mathieson model, Dunhem&Came model, Kaker&Ocapu model and Central Institute of Aviation Motors (CIAM, Russia) model. Using them, the calculation results were compared with experimental data for 170 airfoil cascades of axial turbines. These cascades include a diversity of blade profiles of axial turbines used in aircraft gas turbine engines. Direct comparison of the calculated and experimental results did not make it possible to uniquely choose the best model. For this reason, the analysis method of loss models based on the statistical analysis of calculation and experimental data deviation was developed. It is shown that the deviations are subject to the normal distribution law. Based on the analysis of mathematical expectations μΔζ and standard deviation σΔζ, it was found that CIAM model gives the results closest to the experimental data. It shows the deviation from the real values of the loss 2±82% with a probability of 95%.
Selection of Models to Assess the Profile Losses in Blade Rows Using the Methods of Mathematical Statistics
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Baturin, O, Kolmakova, D, Gorshkov, A, & Popov, G. "Selection of Models to Assess the Profile Losses in Blade Rows Using the Methods of Mathematical Statistics." Proceedings of the ASME 2015 Gas Turbine India Conference. ASME 2015 Gas Turbine India Conference. Hyderabad, India. December 2–3, 2015. V001T02A003. ASME. https://doi.org/10.1115/GTINDIA2015-1245
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