Abstract
The aim of this paper is to improve the efficiency of a low pressure compressor within a turbojet engine. For this purpose a new feedback controller will be introduced which compares the actual compressor surge margin to a given reference value. Then, this new feedback controller calculates a deviation on the existing nozzle area schedule such that the overall efficiency of the controller is improved at steady state condition. The major contribution of this work consists in a robust control design approach leading to improved robustness properties and reduced calibration efforts for the controllers of future unmanned aircraft propulsion systems.
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