Cooling Model Calibration in a Collaborative Turbine Preliminary Design Process Using the NASA Energy Efficient Engine Part II: 1D Turbine Modeling

Abstract

Accurately estimating turbine cooling requirements at a preliminary design stage is crucial for modeling the overall propulsion 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. However, for next-generation aero-engines this empirical data becomes outdated. An alternative semi-empirical approach based on an established cooling model is built into a collaborative turbine preliminary tool chain to address this challenge. This cooling model is calibrated for the two cooled high-pressure turbines developed by P&W and GE within the NASA Energy Efficient Engine (E3) program and the resulting data is discussed. Sensitivity studies provide a better understanding of how turbine preliminary design parameters, material and cooling technologies affect cooling requirements. This work focuses on the turbine level studies with an accompanying paper at propulsive system level.