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Simulation of Temperature Field Redistribution Through Multistage Cooled Turbines

[+] Author Affiliations
A. V. Granovski, M. K. Kostege


M. Ja. Ivanov, R. Z. Nigmatullin

Central Institute of Aviation Motors (CIAM), Moscow, Russia

Paper No. 2001-GT-0576, pp. V001T03A087; 8 pages
  • ASME Turbo Expo 2001: Power for Land, Sea, and Air
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • New Orleans, Louisiana, USA, June 4–7, 2001
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7850-7
  • Copyright © 2001 by ASME


The paper presents the detail investigation of temperature field evolution through multistage cooled turbines. An investigation bases on simple enough numerical simulation and allows for transient, heat transfer, viscous and some other important effects on temperature field transformation. Herewith the special test data for a number of cooled turbines are used.

The developed numerical code has the following peculiarities:

- a time-marching method for the unsteady Euler equation system;

- a special algorithm of flow parameters averaging in mixing planes in the middle of axial gaps;

- a monotone implicit scheme of second or third order accuracy in space and time.

The code has been used for a numerical study of the flow pattern in a number of multistage aviation and industrial turbines. The described simulation demonstrates satisfactory correlation between the numerical and experimental data for temperature gradient attenuation in the flowpath of investigated cooled turbines.

Copyright © 2001 by ASME



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