Aircraft Single-Jet Engine with Hydro-Mechanical Thrust Augmentation System Based on Coolant Injection into the Compressor

Abstract

The paper deals with a complex control system of a two-spool single-jet aircraft engine equipped with a coolant injection system into its compressor. The author has defined control system's architecture (consisting of a fuel controller, an exhaust nozzle controller, embedded with a coolant injection controller) and, based on it, has established system's mathematical model. Embedded control system's input and output parameters were established and system's block diagram with transfer functions was built. A study concerning system's quality was performed (embedded system's step response) and some conclusions were presented.