Control Laws of the Aviation Gas Turbine Engine

Abstract

The article is devoted to the solution of an important scientific and applied problem of improving the dynamic characteristics of an aviation engine and ensuring flight safety and the efficiency of aircraft operation, taking into account the properties of adaptive control of an aviation gas turbine engine: <structure><functioning><adaptation><development>. Based on the concept of creating perspective aviation engines with an increased level of control automation and with units operating at elevated temperatures and protected from high-energy electromagnetic radiation, the basic laws of controlling an aviation gas turbine engine in throttle modes, low-throttle mode, gas intake and discharge modes, and start-up mode are defined. To improve the working process of the engine, it is proposed to use the gas turbine engine control system as a mechatronic system based on the principle of adaptation. With the help of the Laplace transformation, the dynamic characteristics of the power plant were determined and the mathematical model of the power plant was investigated as a constructive aspect of the automatic control system. The gas turbine and the supersonic air manifold can to some extent be considered as independent control objects, replacing the connections between them with disturbing influences. For the control and limitation circuits, it is necessary to create control programs that calculate the values of the control parameters of the turbocharger rotor speed and gas temperature behind the turbine. Regulation of fuel consumption is carried out according to the derivative of the control parameters.