Оptimization of gas turbine aircraft engine control throughout the engine service life


The task of optimizing control methods in order to maintain key performance parameters of a gas turbine engine throughout the engine service life is considered. Variations in the performance characteristics of engine components in the process of operation are analyzed. To study the effect of deterioration on the engine parameters, a mathematical model of a turbofan engine was modified. The influence of degradation of the gas turbine engine components on its key performance parameters with traditional control methods is assessed. An engine control method using the value of thrust calculated in the on-board engine mathematical model is proposed. This method makes it possible to compensate for the negative effect of the components’ performance degradation due to their wear. The results of mathematical modeling of the operation of a turbofan engine in steady-state and transient modes are given. The results confirm the effectiveness of the proposed control method: despite the engine deterioration the original thrust value is maintained due to the available gas temperature margin in the combustion chamber

About the authors

O. S. Gurevich

Central Institute of Aviation Motors

Author for correspondence.
Email: gurevich_os@ciam.ru

Russian Federation

Doctor of Science (Engineering), Professor
Deputy Director General

F. D. Golberg

Central Institute of Aviation Motors

Email: fegolb@ciam.ru

Russian Federation

Doctor of Science (Engineering), Professor
Head of Section

S. A. Smetanin

Central Institute of Aviation Motors

Email: smetaninsa@ciam.ru

Russian Federation

Head of Section

M. E. Trifonov

Central Institute of Aviation Motors

Email: mtrifonov@ciam.ru

Russian Federation



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Abstract - 67

PDF (Russian) - 58

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