More integrated gas turbine engine controller design

The paper presents a novel application of evolutionary algorithms to the problem of integrated control system design for gas turbine aero-engines. Using a multiobjective evolutionary algorithm, candidate control configurations are tested on a model of an aircraft engine to assess performance, safety, stability and other design criteria. An example controller integration design problem, considering some of the problems likely to be associated with new variable cycle engine concepts, is considered demonstrating aspects of the proposed approach that allows many design objectives from different disciplines to be considered in parallel. Potential closed loop control configurations are evaluated and compared with one another within an optimization framework. As a result of this analysis it is shown how informed decisions may be made regarding the nature of the control employed, acceptable performance margins and elements of the engine design.