Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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A search for recommendations to select numerical model settings for efficient simulation of the working process of the axial turbine blade with convective cooling

Published: 27.11.2023

Authors: Volkov A.A., Popov G.M., Zubanov V.M., Matveev V.N., Baturin O.V.

Published in issue: #11(143)/2023

DOI: 10.18698/2308-6033-2023-11-2316

Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts

Currently, when simulating the cooled turbine operation process, models are introduced that include flow section in the interblade channels, blade body and internal channels of the cooling system. Such models require significant calculation resources and high qualification of the designer. An attempt to simplify the model reduces reliability of the results obtained. Unfortunately, the available technical publications do not provide recommendations on adjusting such calculation models. The presented work provides results of a study aimed at finding optimal settings of the numerical models making it possible to accurately and cost-effectively simulate the associated operation process in the cooled turbines with convective cooling. As a result, practical recommendations were obtained in selection of grid parameters and turbulence models for such problems. Recommendations were generated for adjusting the working process numerical models of the turbine blades with convective cooling in the two-dimensional setting.

[1] Inozemtsev A.A., Nikhamkin M.A., Sandratskiy V.L. Osnovy konstruirovaniya aviatsionnykh dvigateley i energeticheskikh ustanovok [Fundamentals of designing aircraft engines and power plants]. Moscow, Mashinostroenie Publ., 2008, 207 р.
[2] Ho K., Liu J.S., Elliott T., et al. Coupled heat transfer analysis for gas turbine film-cooled blade. In: Proceedings of the ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. Volume 5A: Heat Transfer, 2016, art. no. GT2016-56688, V05AT10A003.
[3] Ke Z., Wang J. Coupled heat transfer simulations of pulsed film cooling on an entire turbine vane. Applied Thermal Engineering, 2016, vol. 109, pp. 600–609.
[4] Insinna M., Griffini D., Salvadori S., et al. Coupled heat transfer analysis of a film cooled high-pressure turbine vane under realistic combustor exit flow conditions. In: Proceedings of the ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. Volume 5A: Heat Transfer, 2014, art. no. GT2014-25280, V05AT11A007.
[5] Wróblewski W. Numerical evaluation of the blade cooling for the supercritical steam turbine. Applied Thermal Engineering, 2013, no. 51, рр. 953–962.
[6] Bonini A., Andreini A., Carcasci C., et al. Coupled heat transfer calculations on GT rotor blade for industrial applications: Part I—Equivalent internal fluid network setup and procedure description. In: Proceedings of the ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. Volume 4: Heat Transfer, Parts A and B, 2012, art. no. GT2012-69846, рр. 669–679.
[7] Shevchenko I.V., Rogalev N., Rogalev A., et al. verification of thermal models of internally cooled gas turbine blades. International Journal of Rotating Machinery, 2018, Special Issue. Article ID 6780137.
[8] Duchaine F., Corpron А., Pons L. Development and assessment of a coupled strategy for coupled heat transfer with Large Eddy Simulation: Application to a cooled turbine blade. International Journal of Heat and Fluid Flow, 2009, no. 30, рр. 1129–1141.
[9] Hylton L.D., Mihelc M.S., Turner E.R., et al. NASA technical report: NASA-CR-168015, 1983.
[10] Popov G., Matveev V., Baturin O., et al. Selection of parameters for blade-to-blade finite-volume mesh for CFD simulation of axial turbines. MATEC Web of Conferences, 2018, vol. 220.