In order to reduce the aerodynamic loss caused by leakage in tip gap of the turbine rotor blade and improve the film cooling efficiency on the blade tip

discretely arranging the rib labyrinth at the squealer tip was proposed.According to the structure of a turbine's rotor blades

the cascade test bench was designed to detect the film cooling efficiency of the rib labyrinth gap.The gas film cooling efficiency of both the labyrinth tip and the groove tip was measured by steady-state liquid crystal display technology

at blowing ratio of 1.0

1.5and 2.0and the gap height of 1.0%

2.0% and 3.0%.The results show that

with an increase in the blade tip height

the average film cooling efficiency of both the above two structures decreased.Within a certain range of tip height and blowing ratio

the film cooling efficiency of the labyrinth tip can be 63%higher than that on the squealer tip at the most.The labyrinth dramatically increased the cooling range of the tip and enhanced the cooling efficiency

which made the cooling efficiency be more even.