In order to meet the development needs of the internal cooling structure of gas turbine blades, this paper researches the jet impingement cooling in a limited space. Numerical simulation method is employed to obtain the flow field details and analyze the flow and heat transfer mechanism. The heat transfer coefficient distribution of the target surface is obtained by the transient liquid crystal, which verifies the accuracy of the CFD results. The effects of inlet mass flow rate m˙in, rows of jet holes N, jet hole diameter Dj, jet-to-target distance H/Dj and transverse distance between jet holes S/W are considered. The results show that: The flow and heat transfer characteristics at different m˙in are qualitatively similar. N has a significant effect on the heat transfer coefficient and total pressure difference. With the increase of N, the heat transfer coefficient and the total pressure difference decrease. Dj has obvious effect on heat transfer coefficient and total pressure difference. As Dj increases, both the heat transfer coefficient and the total pressure difference decrease. H/Dj has only a slight effect on the heat transfer coefficient and total pressure difference. When H/Dj increases from 1.2 to 2.2, the heat transfer coefficient increases and the total pressure difference decreases. When H/Dj increases from 2.2 to 3.2, the heat transfer coefficient decreases and the total pressure difference is almost unchanged. The effect of S/W on the heat transfer coefficient and total pressure difference is more obvious than that of H/Dj. The heat transfer coefficient and total pressure difference are the largest when S/W = 0.5. The structure with N = 8,Dj = 24 mm,H/Dj = 2.2,S/W = 0.5 has the best comprehensive heat transfer performance under the range of the boundary condition.
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