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.
Highlights
The development of aviation gas turbine engines (AGTE) at the present stage is mainly reached by assimilation of high values of gas temperature in front of the turbine ( TГ )
The activities on gas temperature increase are conducted in several directions
Assimilation of high ( TГ ) in AGTE is reached by refinement of cooling systems of turbine blades
Summary
The development of aviation gas turbine engines (AGTE) at the present stage is mainly reached by assimilation of high values of gas temperature in front of the turbine ( TГ ). At allowed values of AGTE metal temperature Tlim = (1100...1300K ) , the absolute error of temperature calculation should be in limits ( 20 - 30K ), that is no more than 2-3%. This is difficult to achieve (multiconnected fields with various cooling channels, variables in time and coordinates boundary conditions). Such problem solving requires application of modern and perfect mathematical device
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