Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module

An approach for preliminary aero-engine design, incorporating a mean-line code the design of axial-flow, multi-stage compressors, is presented. The compressor developed and integrated within framework assessment concepts. It then combined with modules map generation, multi-point engine steady-state transient off-design performance aircraft mission analysis. Implementation examples are presented, demonstrating determination optimal combination parameters achieving minimum fuel burn over specific mission, while obeying constraints that guarantee operability entire flight envelope. Constraints related to stability during maneuvers between idle static take-off conditions temperature limits at maximum respected by final design. results demonstrate potential trade-offs level aerodynamic stability.