Методология оптимизации параметра согласования совместной работы камеры сгорания и турбины

A. V. Grigoriev; Григорьев А. В.; P. P. Golubchikov; Голубчиков П. П.; M. Yu. Ilushin; Илюшин М. Ю.; O. A. Rudakov; Рудаков О. А.; A. V. Solovieva; Соловьева А. В.

doi:10.18287/2541-7533-2011-0-3-2(27)-106-111

Methodology of optimization of parameter of matching the combustion chamber and turbine joint operation

Authors: Grigoriev A.V.¹, Golubchikov P.P.¹, Ilushin M.Y.¹, Rudakov O.A.¹, Solovieva A.V.¹
Affiliations:
1. Klimov JSC
Issue: Vol 10, No 3-2 (2011): Special Issue
Pages: 106-111
Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
URL: https://journals.ssau.ru/vestnik/article/view/6792
DOI: https://doi.org/10.18287/2541-7533-2011-0-3-2(27)-106-111
ID: 6792

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Abstract

For the purpose to provide the fuel efficiency and the engine reliability the article analyses characteristics of the temperature field, the fuel flow turbulence downstream of the combustion chamber, depth of the nozzle guide vanes cooling in their interconnection on the basis of optimization of the value of the corrected gas flow rate upstream of the turbine as a matching parameter of the joint operation of these thermal and gas dynamic units taking the effective efficiency of the engine thermo-dynamic cycle as a goal function considering the strength limit of the rotor blades.