This paper aims to develop and describe control theoretic concepts for distributed control of gas turbine engines, and also to develop a dynamic engine model incorporating distributed components in compressor dynamics, engine cycles, and engine control. Concepts and architectures for distributed control are developed that create tangible benefits from the distribution of closed loop feedback around the engine. Engine dynamics has been divided into two main subsystems including Fan and core subsystems. Separate controllers have been designed for each subsystem. Fuel flow is the control input for the core subsystem, and fan vane angle (or fan exit area) is the control input for the fan subsystem. For each subsystem linear and adaptive controllers are designed. Simulation results indicate that the developed distributed controllers are operating properly. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
|Original language||English (US)|
|Title of host publication||AIAA Guidance, Navigation, and Control Conference and Exhibit|
|Publisher||American Institute of Aeronautics and Astronautics Inc.email@example.com|
|State||Published - Jan 1 2009|