Embedded control system for an aircraft two-spool jet engine with coolant injection into the compressor

The paper deals with an aircraft two-spool single-jet engine's control system; basic control system (based on a fuel flow controller and an exhaust nozzle controller) is completed by a new controller (of the injected coolant flow rate). The paper has studied possible engine control architecture and established its mathematical model. Considering the engine as controlled object and its thrust the most important operation effect, one has chosen as main outputs spools' rotational speeds, as secondary output the combustor's temperature, while as single input — engine's power lever displacement. Based on embedded system's main parts' mathematical models, the author has described the embedded control system by its block diagram with transfer functions; furthermore, some Simulink-Matlab simulations are performed, concerning embedded system quality (its output parameters time behavior) and, meanwhile, some conclusions concerning engine's parameters mutual influences are revealed.