Numerical Investigation on 3D Hydrogen-Fueled Combusting Flow Within Turbine Blade Passage (1st Report, Influence of Injector-Hole Layout)

Abstract

We have investigated jet engines, in which hydrogen fuel is injected from turbine blade surface and combusted within turbine blade passages. Although these hydrogen-fueled propulsion systems are expected to have higher power, lighter weight and lower emissions, it still has many problems to be solved. In the previous studies, it was found that blade surface temperature exceeds the allowable temperature limit. Therefore, it is necessary to investigate the flow field with hydrogen combustion and the cooling method which prevents structure materials from melting down. The objective of this study is to clarify the influence of the injector-hole layout on the characteristics of the 3-dimensional flow field with hydrogen-fueled combustion within a turbine blade passage. Reynolds-averaged compressible Navier-Stokes equations are solved with incorporating a turbulence and a reduced chemical mechanism models. Using the computational results, the 3-dimensional turbulent flow field with chemical reactions is visualized and investigated. Additionally, the film cooling effect and the aerodynamic performance of the blade are estimated.