05 - Propulsion
KNOWLEDGE-BASED TURBINE DISK MODELING – A CONCEPTUAL DESIGN PROCESS CALIBRATED TO THE NASA ENERGY EFFICIENT ENGINE
P. Wehrel¹, J. Schmeink¹, J. Häßy¹; ¹German Aerospace Center (DLR), Germany
Rotating disks are essential components of every turbomachinery. Since the disks account for a significant portion of the total engine weight, turbomachinery disk design is crucial and has to be already considered in the early phase of conceptual design, which is a highly challenging task due to many uncertainties. Especially the tradeoff between disk mass and life time is a critical aspect that has to be handled carefully. In order to facilitate this task for engineers, this paper provides calibrated design parameters for turbine disks which are derived from the NASA Energy Efficient Engine (E3). Performance and geometry models are generated for the high- and low-pressure turbine of the NASA E3 and a conceptual disk design process is calibrated based on these models. The design process itself follows the methodology of knowledge-based geometry and mass estimation. Important results are the generation of suitable reference geometries as well as the determination and quantification of dimensionless parameter sets for disk parametrization. Moreover, blade and disk masses are calculated and a conceptual disk stress analysis is performed in order to provide knowledge-based safety factors.