Preliminary Multi-Disciplinary Optimization in Turbomachinery Design

Abstract

The gas turbine engine is a complex aerodynamic machine with performance, structural and manufacturability challenges. This paper gives an overview of a multidisciplinary optimization approach applied to the conceptual design of small aircraft engines. A description of major turbomachinery disciplines and the numerous interactions between disciplines is given followed by a discussion of the need for preliminary design optimization. The approach to development of such a system undertaken at Pratt & Whitney Canada is described including identification of appropriate design tools and their influence on the geometrical definition of an engine cross-section. Finally, preliminary optimization results are presented.