In order to evolve aeroengine overall performance design from the deterministic design to the probabilistic design

an aeroengine cycle optimization design approach for multiple operating conditions performance reliability based on distributed cooperative response surface method (DCRSM) was proposed. The turbofan engine simulation model with uncertainty component performance was established as an example. The distributed response surface models of thrust and special fuel consumption performance under several typical operating conditions were established by the experimental design and the off design point performance simulation

and then the cooperative response surface model was established for cycle optimization. The non inferiority solution set of the cycle parameters was generated from optimization and verified by the random trial. The results showed that the all cycle parameters from the non inferiority solution set could make the engine overall performance achieve a high reliability of not less than 97.5% simultaneously under all expected operating conditions. From the non inferiority solution set obtained by multiple operating conditions performance reliability cycle optimization method

the most suitable cycle selection can be decided according to the physical truth in engine preliminary design phase.