An Adaptive Fuzzy Gas-Turbine Engine Combustion-Chamber Temperature Meter

• Published in: Russian electrical engineering Vol. 93; no. 11; pp. 685 - 689
• Main Authors: Yuzhakov, A. A., Hizhnyakov, Yu. N., Storozhev, S. A., Nikulin, V. S.
• Format: Journal Article
• Language: English
• Published: Moscow Pleiades Publishing 2022; Springer Nature B.V
• Subjects: Aircraft; Aircraft engines; Combustion chambers; Engineering; Gas turbine engines; Machines; Manufacturing; Processes; Static characteristics; Temperature measurement; Thermocouples; gas-turbine aircraft engine; combustion chamber; fuzzy control; adaptive fuzzifiers; fuzzy composition; Sugeno equations; fuzzy implication; homogeneous manifold (collector); temperature meter
• ISSN: 1068-3712; 1934-8010
• DOI: 10.3103/S106837122211013X

To measure the temperature in the combustion chamber of a gas-turbine aircraft engine, it is proposed to use a virtual fuzzy meter based on changing the rotation parameters of gas turbines, taking into account the combustion of fuel supplied by a differential manifold. The meter architecture is built according to the classical scheme: a fuzzifier using sigmoid membership functions, a fuzzy inference block containing operations of fuzzy implication, a fuzzy composition, and a defuzzifier. Adaptation of the fuzzy temperature meter was performed using the method of sequential learning, and the study of the static properties of the meter was carried out using a mathematical model on the MATLAB platform. According to the oscillogram, where the comparison was carried out as a result of measurements with a thermocouple, we can conclude that the static characteristic of the adaptive fuzzy temperature meter is linear. It is possible to use the developed temperature meter to control the homogeneous collector of the combustion chamber and control the temperature in the first zone of the combustion chamber in order to control the temperature of vibration combustion and breakdown. The main advantage of the developed temperature meter lies in constant temperature measurement during the operation of the aircraft.