Publication de 18 numéros par an
ISSN Imprimer: 1064-2285
ISSN En ligne: 2162-6561
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1.7
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1.4
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0.6
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0.00072
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0.43
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0.318
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3.5
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HEAT LOAD DISTRIBUTION OF THE SQUEALER TIP WITH SHROUD COOLANT INJECTION
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RÉSUMÉ
In this paper, the aerothermal performance of a cavity tip is numerically investigated with shroud coolant injection in an axial flow turbine. Cooling air is injected through a row of discrete holes located at upstream of approximately 1.4% Cax length from the leading edge (LE) of blade in the shroud. The relative leakage flow rate, heat transfer of tip, and total pressure loss coefficient are selected for the detailed performance analysis, and the tip cavity depth and shroud coolant blow ratio are the research parameters. The results show some of the shroud coolant enters gap, and become confluent with the leakage flow, which increases energy dissipation of the fluid in the cavity, and the local high heat transfer region decreases obviously at the cavity bottom near LE. For the heat transfer coefficient h on the squealer tip with shroud coolant injection, the cavity depth remains a prominent factor. The area of a region with a high h value at the cavity bottom can be reduced by up to 75.72% with increasing cavity depth. The area-averaged heat transfer coefficient have and the inhibition to leakage flow are not sensitive to the blowing ratio of the shroud coolant.
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