TY - JOUR
TI - Numerical study on film cooling and convective heat transfer characteristics in the cutback region of turbine blade trailing edge
AU - Xie Yong-Hui
AU - Ye Dong-Ting
AU - Shen Zhong-Yang
JN - Thermal Science
PY - 2016
VL - 20
IS - 13
SP - 643
EP - 649
PT - Article
AB - Gas turbine blade trailing edge is easy to burn out under the exposure of  high-temperature gas due to its thin shape. The cooling of this area is an  important task in gas turbine blade design. The structure design and analysis  of trailing edge is critical because of the complexity of geometry,  arrangement of cooling channels, design requirement of strength, and the  working condition of high heat flux. In the present paper, a 3-D model of the  trailing edge cooling channel is constructed and both structures with and  without land are numerically investigated at different blowing ratio. The  distributions of film cooling effectiveness and convective heat transfer  coefficient on cutback and land surface are analyzed, respectively. According  to the results, it is obtained that the distributions of film cooling  effectiveness and convective heat transfer coefficient both show the  symmetrical characteristics as a result of the periodic structure of the  trailing edge. The increase of blowing ratio significantly improves the film  cooling effectiveness and convective heat transfer coefficient on the cutback  surface, which is beneficial to the cooling of trailing edge. It is also  found that the land structure is advantageous for enhancing the streamwise  film cooling effectiveness of the trailing edge surface while the film  cooling effectiveness on the land surface remains at a low level. Convective  heat transfer coefficient exhibits a strong dependency with the blowing  ratio, which suggests that film cooling effectiveness and convective heat  transfer coefficient must be both considered and analyzed in the design of  trailing edge cooling structure.