| Citation: | DONG Qi, QIU Changbo, YU Qiang, et al. Effect of cooling stream injection on cooling characteristics of guide blade endwall[J]. Journal of Aerospace Power, 2023, 38（8）：1946-1955 doi: 10.13224/j.cnki.jasp.20220807
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In order to study the effect law of the cooling jet structure at the leading edge of turbine guide blade endwall on the film cooling characteristics at endwall, four jet structures were designed. The effect of cooling jet geometric and aerodynamic parameters on the adiabatic wall temperature at the endwall was studied by a method of combining test and numerical simulation to obtain the following conclusions: the low-temperature region of the endwall presents a “curved triangle” feature, namely, along the air flow direction in the cascade channel, the low-temperature region decreases sharply and deflects substantially toward the blade suction surface, and finally disappears at the trailing edge of the blade suction surface, while an optimal cooling jet structure exists at the leading edge of the endwall, that is, when the cooling air outflow area ratio is 0.072 and the jet orifice area ratio is 2.0, the maximum adiabatic cooling efficiency at the endwall can reach 0.325; the jet ratio has a great influence on the adiabatic cooling efficiency of the endwall. With the increase of the jet ratio, the adiabatic cooling efficiency at the endwall gradually increases, while the position where the maximum adiabatic cooling efficiency at the endwall occurs shifts toward the pressure surface.Within the area near the leading edge of the endwall, the temperature ratio has little effect on the adiabatic cooling efficiency, and the change range is less than 0.01, but within the area away from the leading edge, the adiabatic cooling efficiency increases with the increase of the temperature ratio, and the maximum increase is about 0.03.
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