Conjugate Heat Transfer for LES of Gas Turbine Engines

Sponsor: U.S. Navy

Collaborator: Cascade Technologies

One of the challenges in predicting turbine blade temperatures is to accurately capture the conjugate nature of the heat transfer, which involves complex internal cooling technologies as well as external film-cooling. While turbine cooling has evolved over many decades, there are tradeoffs that also need to be assessed in terms of overall aerodynamic efficiencies of a turbine stage. The aerodynamic efficiency of a turbine stage is highly dependent upon the losses incurred by the external film-cooling features, in particular. This proposed effort is to provide test cases that lead to the development of large eddy simulations relevant to predicting turbine cooling and aerodynamic efficiency. The LES modelling will be completed by Cascade Technologies.