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Numerical modeling of gas turbine cooled blades

Abstract

In contrast to methods that do not take into account multiconnectivity in a broad sense of this term, we develop mathematical models and highly effective combination (BIEM and FDM) numerical methods of calculation of stationary and quasi-stationary temperature field of a profile part of a blade with convective cooling (from the point of view of realization on PC). The theoretical substantiation of these methods is proved by appropriate theorems. For it, converging quadrature processes have been developed and the estimations of errors in the terms of A. Ziqmound continuity modules have been received. For visualization of profiles the method of the least squares with automatic conjecture, device spline, smooth replenishment, and neural nets are used. Boundary conditions of heat exchange are determined from the solution of the corresponding integral equations and empirical relationships. The reliability of these methods is proved by calculation and experimental investigations heat and hydraulic characteristics of the gas turbine first stage nozzle blade.


First Published Online: 14 Oct 2010

Keyword : multiconnected systems, method of the boundary integrated equations, splints, neural networks

How to Cite
Pashayev, A., Askerov, D., Sadiqov, R. A. C. oqlu, & Samedov, A. (2005). Numerical modeling of gas turbine cooled blades. Aviation, 9(3), 9-18. https://doi.org/10.3846/16487788.2005.9635905
Published in Issue
Sep 30, 2005
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This work is licensed under a Creative Commons Attribution 4.0 International License.