Control Actuation and Simulation of Pseudo FADEC of Advanced Turbo Fan Aero-Engine

Control actuation of advanced aero-engine requires high speed processing of signals received from various sensors mounted on the aero-engine for health monitoring, performance control and optimization of critical parameters that are governed by control program. The present work is aimed in developing the logic of control and actuation by the pseudo- Full Authority Digital Engine Control (FADEC) for the advanced twin spool aero-engine and regulate the key performance parameters like Low Pressure Compressor Rotor (LPCR) speed N
₁
, High Pressure Compressor Rotor (HPCR) speed N
₂
, Exhaust Gas Temperature (EGT) T
₄
based on the ambient input temperature (T
₀₁
). This paper demonstrates the control logic of different section of the HPCR (N
₂
) verses T
₀₁
of the advanced aero-engine using SIMULINK and the simulation results are reproduce.