Combustion chamber gas temperature level calculation of turbo-jet fan engine with afterburning chamber for algorithm development

Abstract

In the present paper is represent the influence analysis of gas temperature level before the turbine (T*Г), in the engine thrust-economic activities. With the use of engine mathematical model (dynamic and non-linear), was made a research, shows the influence of technical state deterioration during the operation on the T*Г value. There were represented results of mathematic model identification by the data of engine’s development testing on the steady and transitional modes/ Engine management was examined by the law T*Г =const, based on establishing of non-measurable parameter T*Г in the real time, which was found under regression model by the meaning of standard enginesensors; there also was made minimization of defined regression model by the regularity criteria value. We also perform adequacy estimation of computing T*Г by theregression model, and sensitivity of this model to the instrumentation accuracy.