Design And Performance Study Of Internal Cooling Structure Of Gas Turbine Blade

With the increase of inlet temperature of gas turbine in recent years,the research on blade cooling technology has become more and more important.This paper first focuses on the internal cooling structure of stationary blade of gas turbine and designs a u-shaped symmetrical bifurcated internal cooling channel based on Murray's law.Through the numerical simulation method,compared with traditional direct channel and serpentine channel,it is found that the comprehensive performance factor is 1.16 times of the direct channel and 5.76 times of the serpentine channel,it shows that its comprehensive performance has obvious advantage over the traditional channel.Secondly with ANSYS Fluent software for Mark ?blade which been studied experimentally by Hylton et al.in number 5411 transonic experimental conditions to conduct numerical simulation of fluid-solid coupling heat transfer problem.SST k-? turbulence model is adopted to deal with shock wave and transition in flow field.Compared with the experimental data,it is found that Fluent has a good accuracy in qualitative analysis of this problem.In quantitative analysis,the simulation of temperature value is relatively accurate with a maximum deviation of 5.1%,and the pressure value has a maximum deviation of 25.7% in the flow complex area.Finally apply new channels to Mark? blade,compared with original Mark ? blade simulation results found that the cooling efficiency increases by about 33%,the cooling uniformity is better,and improve the thermal stability of blade.In addition,the steam cooling of new internally cooled blade was studied,it was found that the cooling efficiency of steam cooling was 16.9% higher than that of air cooling under the same conditions.The flow rate and temperature at the steam inlet have a certain influence on the cooling efficiency of the blade,and there is an optimal value within its value range to maximize the cooling efficiency.