间隙位置和几何对端壁冷却性能的影响

doi:10.7527/S1000-6893.2017.620942

Abstract

Abstract:

The effects of the location and geometry of the upstream slot on the end-wall film cooling performance of a gas turbine blade are numerically investigated by solving three-dimensional Reynolds-Averaged Navier-Stokes (RANS) equations coupled with the k-ω turbulence model. Based on the accuracy validation of the numerical method, the effects of three slot locations on the film cooling effectiveness of the end-wall are numerically analyzed. Three convergent trapezoid slot models are proposed, and the effect of these models on the end-wall flow and cooling characteristics are investigated. The results indicate that the increase of the distance between the slot and the blade leading edge reduced the film cooling effectiveness of the region near the leading edge influenced by the horseshoe vortex, but when the mass flow ratio (M) is larger than 1.0%, the uniformity of the film cooling effectiveness distribution is improved. When M=0.5%, the slot locating at the position 0.1 times axial chord away from the blade leading edge resulted in the ingestion of mainstream flow. Comparing with the nominal slot, the three convergent trapezoid slot models improved the end-wall film cooling effectiveness significantly. Especially for M=1.0%, the greatest improvement of end-wall average film cooling effectiveness is as much as 105.36% with the convergent trapezoid slot models. Besides, the models prevented the ingestion of mainstream flow when M=0.5%.

Key words: end-wall cooling, slot purge flow, film cooling, numerical simulation, high temperature blade

CLC Number:

V232.4

ZHU Peiyuan, SONG Liming, LI Jun, FENG Zhenping. Effects of location and geometry of slot on film cooling performance of end-wall[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(9): 520942-520942.

References

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Effects of location and geometry of slot on film cooling performance of end-wall

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