The turbomachinery industry is continuously focusing on increasing the efficiency of its equipment. The gas turbine is one of the major pieces of equipment in the industry. It has extensive applications in such areas as power generation, jet propulsion, gas compression, etc. The efficiency and power output of the gas turbine depends on its inlet temperature. Therefore, the modern gas turbine inlet temperature began to exceed the permissible operating temperature of its blade material. Hence, various cooling methods such as dimple cooling, tubulated rib cooling, pin-fin cooling, and jet impingement cooling have been applied to ensure the performance and life of the turbine blade. This study considers the jet impingement cooling for the turbine blade internal cooling. The nozzle plate has 36 both in-line and staggered cylindrical holes. The experiment is completed with standoff distances of 3D and 5D, with the Reynolds number of up to 2000, where D is the nozzle diameter. The numerical study considered only 3D standoff distance, with Reynolds number of up to 8000. Different complex flow and heat transfer phenomena have been described.
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Nourin et al. (2020) studied this question.
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