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首页> 外文会议>ASME turbo expo: turbine technical conference and exposition >NUMERICAL STUDY ON EFFECTS OF JET NOZZLE ANGLE AND NUMBER ON VORTEX COOLING BEHAVIOR FOR GAS TURBINE BLADE LEADING EDGE
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NUMERICAL STUDY ON EFFECTS OF JET NOZZLE ANGLE AND NUMBER ON VORTEX COOLING BEHAVIOR FOR GAS TURBINE BLADE LEADING EDGE

机译：射流喷嘴角度和数量对燃气轮机叶片前缘涡流冷却性能的数值研究

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摘要

Vortex cooling is a promising blade cooling technique for its excellent heat transfer and pressure loss control behavior. In this paper, the proper vortex chamber model is utilized for vortex cooling mechanism analysis. Three dimensional viscous steady Reynolds Averaged Navier-Stokes (RANS) equations are adopted to explore the influences of jet nozzle angle and number on vortex cooling flow and thermal performance. Turbulence model verification and grid independence analysis are conducted to determine the suitable turbulence model and mesh number for calculations. Results show that due to obvious mass flux enhancement downstream, stronger axial impact effect will generate, leading to the high Nusselt number region downstream deflection towards outlet. As jet nozzle angle increases from α＝60° to α＝120°, the static pressure ratio increases for the upstream region and decreases for the downstream region, and the total pressure loss ratio increases. The rotation movement and heat transfer intensity will decrease when jet nozzle angle changes away from α＝90°. The air jetting velocity decreases and the static pressure ratio increases with the increasing jet nozzle number. When jet nozzle angle increases from 1 to 11, the total pressure loss ratio decreases and the heat transfer intensity increases at first and then decreases.
机译：涡旋冷却是一种很有前途的叶片冷却技术，因为它具有出色的传热和压力损失控制性能。在本文中，适当的涡流室模型被用于涡流冷却机理分析。采用三维粘性稳态雷诺平均纳维斯托克斯（RANS）方程来研究喷嘴角度和数量对涡流冷却流和热性能的影响。进行湍流模型验证和网格独立性分析，以确定合适的湍流模型和网格数进行计算。结果表明，由于下游明显的质量通量增强，将产生更强的轴向冲击效果，从而导致较高的努塞尔特数区域下游向出口偏转。当喷嘴角度从α＝ 60°增大到α＝ 120°时，上游区域的静压比增加，下游区域的静压比减小，总压力损失比增加。当喷嘴角度偏离α＝ 90°时，旋转运动和传热强度会降低。随着喷嘴数量的增加，空气的喷射速度降低，静压比增加。当喷嘴角度从1增大到11时，总压力损失率减小，传热强度先增大，然后减小。

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