COUPLING OF PREDESIGN AND PERFORMANCE TOOLS FOR TRANSIENT AIRCRAFT ENGINE ANALYSES

Abstract

Aero-engine performance is facing increasing demands with respect to thrust requirements, ratings and operational reliability. By that, it places a heavy burden especially on transient engine behavior. Evaluating this transient performance early in the design process of aero-engines aids to reduce the immense costs accompanied with engine development. For that purpose it is inevitable to integrate predesign and transient performance tools to give a more holistic view of tolerable new engine concepts. In the present paper, a methodology for the direct coupling of preliminary engine design and transient performance via a central data model is presented. This methodology is explored at the example of a high-pressure compressor (HPC) similar to the one used in the IAE V2500 turbofan. Predominant transient performance phenomena such as rotor inertia, heat soakage and tip clearance changes in the turbo-components are captured in this process chain. Furthermore, effects of aerodynamic design changes of the HPC on engine s acceleration are investigated.