Математичне моделювання робочих процесів авіаційного газотурбінного двигуна ТВ3-117 для контролю і діагностики його технічного стану

The subject matter of the article is TV3-117 aircraft engine and methods for monitoring and diagnosing its technical condition. The goal of the work is development of a method of control and diagnostics of TV3-117 aircraft engine technical state in flight modes with the use of mathematical modeling of its working processes. The following tasks were solved in the article: getting the system of equations describing the workflows of the aircraft engine TV3-117; differential approximation of equations describing the workflows of the aircraft engine TV3-117; development of algorithm for implementation of differential approximation of the equations of work processes occurring in the aircraft engine TV3-117. The following methods used are – mathematical modeling methods, difference approximation method (transition to dimensionless form of equations, difference approximation, transition to linear model in space and mathematical description of the distance between two adjacent points). The following results were obtained – An algorithm for the implementation of the difference approximation of the equations of workflows occurring in TV3-117 aircraft engine has been developed, which allows to simulate situations that could occur during the operation of TV3-117aircraft engine, which provides an opportunity to analyze the past or predict the development of future events in that or other situation. Conclusions: The algorithm for implementing the differential approximation of the equations of workflows flowing in TV3-117aircraft engine, can be used to dynamically display the state of the aircraft engine in real time, that is, to apply it to create a software complex that monitors the dynamic (transient) processes in TV3-117aircraft engine. The scientific novelty of the obtained results is the following: for the first time the method of control and diagnostics of information indicators of TB3-117 aircraft engine technical state was developed, based on the differential approximation of equations describing the workflows occurring in TB3-117 aircraft engine, which will allow to control and real-time diagnostics of thermodynamic parameters. Keywords: aircraft engine, control, diagnostics, Navier-Stokes equation, approximation