タービン翼列間における三次元水素燃焼流の数値的研究 : 第1報,噴出孔配置による影響(熱工学,内燃機関,動力など)

概要

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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.
社団法人日本機械学会の論文
2008-10-25