目的 研究航空发动机或燃气轮机高压涡轮在长时间服役后,其气动性能随叶片表面粗糙度增加的衰退规律。方法 采用高效的点源数值模拟方法,考虑级间机匣、冷气流动及封严气体的影响,同时结合单通道叶栅分区域模拟方法开展相关研究。明确叶片表面粗糙度变化影响气动性能的机理,通过SST湍流模型,研究表面粗糙度大小及分布的变化对高压涡轮气动性能参数的影响规律,预测气动性能衰退程度。计算不同表面粗糙度大小和分布下高压涡轮膨胀比、功率、能量损失及效率等关键参数变化。结果 随着叶片表面粗糙度的增加,高压涡轮效率降低,流动损失增大,一级动叶表面粗糙度对高压涡轮性能参数的影响程度最大。除尾缘区域外,一级动叶的其余区域随着表面粗糙度的增大,无量纲能量损失显著上升。粗糙度对流动损失的影响在喉道前压力面和前缘区域较小,在吸力面和喉道后的压力面区域更显著。在尾缘区域,受尾迹涡的影响,无量纲能量损失随表面粗糙度的增大反而略有减小。结论 叶片表面粗糙度大小和分布对高压涡轮气动性能衰退均有显著影响,粗糙度从Ra=2.4 μm增大到Ra=6.4 μm时,高压涡轮内部流动损失明显上升,效率约下降1%,需要采取适当的叶片表面打磨措施,以减缓涡轮性能的退化。
Abstract
The work aims to investigate the degradation characteristics of aerodynamic performance of high-pressure turbines within aeroengines or gas turbines due to increased surface roughness after long-term service. Relevant researches were conducted with an efficient point-source numerical simulation method that incorporated the effects of turbine center frame section, cooling air flow and sealing gas, in conjunction with a multi-region numerical simulation method for single-passage cascade. The effect of blade surface roughness on aerodynamic performance was clarified, and the SST turbulence model was applied to analyze how variations in the magnitude and distribution of surface roughness affected key aerodynamic performance parameters, thus enabling the prediction of performance degradation trends. The variations in expansion ratio, power, energy loss, and efficiency of high-pressure turbines under different surface roughness and distributions were calculated. With the increase of blade surface roughness, the efficiency of high-pressure turbines decreased and the flow losses increased. The blade surface roughness of the first-stage rotor blade had the greatest impact on high-pressure turbine performance parameters. Except for the trailing edge, the dimensionless energy loss increased markedly in other regions of the first-stage rotor blade with the increasing surface roughness. The impact of roughness on flow losses was relatively smaller in the pressure surface before the throat and at the leading edge, but became more pronounced on the suction side and the pressure side after the throat. In the trailing edge region, due to the effect of wake vortex, the dimensionless energy loss slightly decreased with the increasing surface roughness. Both the magnitude and distribution of blade surface roughness have a significant impact on the degradation of high-pressure turbine aerodynamic performance. When the roughness increases from Ra=2.4 μm to Ra=6.4 μm, the flow losses in the high-pressure turbine increase noticeably, resulting in about a 1% efficiency drop. Therefore, it is necessary to implement appropriate surface finishing measures to mitigate turbine performance degradation.
关键词
涡轮叶片 /
粗糙度 /
气动性能 /
航空发动机 /
能量损失 /
效率 /
数值模拟
Key words
turbine blade /
surface roughness /
aerodynamic performance /
aeroengine /
energy loss /
efficiency /
numerical simulation
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