Knowledge-Based Turbine Disk Modeling - A Conceptual Design Process Calibrated To The NASA Energy Efficient Engine

Abstract

Turbomachinery disks are highly stressed components that contribute significantly to the overall engine mass. Therefore, disk design is crucial and should be already considered in the early phase of conceptual design. In order to advance this field of engineering, this paper proposes a preliminary design process for turbomachinery disks. The process includes the knowledge-based modeling of disk geometries with subsequent mass prediction. Since the temperature has a substantial impact on the material properties and the occurring mechanical stresses, a novel approach for estimating the disk material temperature is also presented. Finally, a stress and burst analysis is performed to evaluate the structural disk integrity. To ensure that the conceptual design process generates reliable results, it is calibrated based on the high- and low-pressure turbine of the NASA Energy Efficient Engine (E3). This additionally enables the determination of knowledge-based design parameters for turbine disks as well as the assessment of safety factors used in stress and burst analysis.