Novel Aero-Engine Multi-Disciplinary Preliminary Design Optimization Framework Accounting for Dynamic System Operation and Aircraft Mission Performance

This paper presents a modular, flexible, extendable and fast-computational framework that implements multidisciplinary, varying fidelity, multi-system approach for the conceptual preliminary design of novel aero-engines. In its current status, includes modules multi-point steady-state engine design, aerodynamic geometry weight, aircraft mission analysis, Nitrogen Oxide (NOx) emissions, control system integrated controller-engine transient-performance analysis. All have been developed in same software environment, ensuring consistent transparent modeling while facilitating code maintainability, extendibility integration at simulation levels. Any workflow can be defined by appropriately combining relevant modules. Different types analysis specified such as sensitivity, experiment optimization. combination parameters selected variables, multi-disciplinary requirements constraints different operating points flight envelope specified. The implementation is exemplified through optimization an ultra-high bypass ratio geared turbofan with variable area fan nozzle, which specific technology limits apply. Although optimum resulted double-digit fuel-burn benefits compared to engines, it did not meet engine-response requirements, highlighting need include assessments early possible phase.