Performance Analysis of Adaptive Control Technique for Aircraft Gas Turbine Engine

This paper presents an adaptive control technique to compensate the thrust variation in an aircraft engine whose performance has been disturbed due to atmospheric conditions. The course of dysfunction appears when a large throttle transient is performed such that the engine switched from low to high speed mode. A relationship is observed between engine disturbance and the overshoot in engine shaft rpm or compressor discharge pressure or turbine temperature, which is determined to cause the thrust variation. This relationship is used to adapt a control. This method works very well up to the operability limit of an engine. Additionally, the type of disturbance identified from sensors data will be useful to implement the adaptive control in real time operation.