抄録
Accurately estimating turbine cooling requirements at a preliminary design stage is crucial for modeling the overall propulsive system. The operating conditions of compressor, combustor and turbine are significantly influenced by these requirements. Empirical cooling models have thus far provided reliable initial estimations. For next-generation aero-engines this solution becomes inadequate. To address this challenge, an alternative semi-empirical approach based on an established cooling model is built into a collaborative turbine design tool chain. This cooling model is applied to the two cooled high-pressure turbines developed by P&W and GE within the NASA E3 program for both validation and to provide calibrated model parameters for future studies. Finally, sensitivity analysis provide a better understanding on how cooling requirements can be reduced through turbine preliminary design decisions, material and cooling technologies. This work focuses on 1D turbine studies with an accompanying paper on 0D engine modeling.
