Abstract
Modern turbojet engines mainly use computerized digital engine control systems. This opens the way for application of advanced algorithms aimed at increasing their operational efficiency and safety. The theory of robust control is a set of methods known for good results in complex control tasks, making them ideal candidates for application in the current turbojet engine control units. Different methodologies in the design of robust controllers, utilizing a small turbojet engine with variable exhaust nozzle designated as iSTC-21v, were therefore investigated in the article. The resulting controllers were evaluated for efficiency in laboratory conditions. The aim was to find a suitable approach and design method for robust controllers, taking into account the limitations and specifics of a real turbojet engine and its hardware, contrary to most studies which have used only simulated environments. The article shows the most effective approach in the design of robust controllers and the resulting speed controllers for a class of small turbojet engines, which can be applied in a discrete digital control environment.
Highlights
Design of control systems for a turbine engine requires knowledge from many science fields, including aerodynamics, fluid mechanics, thermodynamics, rigid body mechanics, chemistry, and material sciences [1]
10 illustrates theresponse response of of the the individual individual controllers in in a laboratory test, test, usingusing the the iSTC-21v engine running on a test bench with a real-time data acquisition control system, with the the iSTC-21v engine running on a test bench with a real-time data acquisition control system, with tested controller implemented in a situational control system without switching, and using only tested controller implemented in a situational control system [20] without switching, and using only a single controller throughoutthe thewhole whole operating operating range engine
The results, obtained in simulation and laboratory experiments, show that a robust control approach can be applied to control the speed of a small iSTC-21v turbojet engine
Summary
Design of control systems for a turbine engine requires knowledge from many science fields, including aerodynamics, fluid mechanics, thermodynamics, rigid body mechanics, chemistry, and material sciences [1]. Operation in aim of the present paper is to show and demonstrate the application of this methodology in an real world conditions is, different from such ideal calculations in a simulated continuous environment with systems, taking into account all the limitations andoperates specifics, as discrete state space, as thephysical measured data are often delayed and controller insuch a discrete state forms robust controllers,represented data delays,byand hits, all were within a variable space.ofSuch uncertainties, datalimited delaysaction or drop-outs, modeled in aoperational distributed envelope. Data delays or dropouts in a distributed state space, as the measured are often delayed andasthe controller operates in a discreteof state control system with impacts data on uncertainty modeling well as stability and performance the space Such uncertainties, represented by data delays or drop-outs, were modeled in a distributed robust control system of a turbine engine were studied in simulated environment [11]. Contrary to most simulation studies presented in the introduction, the result of this study is intended to be a pioneering practical application of robust control in a digital control system of a small turbojet engine, and it may support further developments in the control of such engines in aviation applications
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