基于光场多光谱的涡轮叶片冷却特性实验研究
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1.上海交通大学;2.中国航发湖南动力机械研究所

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国家自然科学基金项目(面上项目,重点项目,重大项目)


Experimental Study on Cooling Characteristics of Turbine Blade Based on Multi-spectral Light-field Thermometry
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1.Shanghai Jiao Tong University;2.Aero-Engine Corporation of China, Hunan Aviation Powerplant Research Institute,;3.Aero-Engine Corporation of China, Hunan Aviation Powerplant Research Institute

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    摘要:

    本文介绍了一种新型光场多光谱测温技术,并将其应用于验证某发动机涡轮叶片复合冷却结构设计的有效性。该测温方法融合多光谱辐射测温与光场成像技术,通过光学滤波片阵列与光场相机的耦合设计,实现了单次快照即可同步采集多波段辐射信息,结合智能优化温度反演算法,有效降低了发射率假设与背景辐射引发的测量误差。相较于传统开槽埋设热电偶的离散点测量方式,该方法可精准获取叶片二维温度场分布,无冷气情况下测温偏差不超过0.33%。实验在主气温度823K条件下获得了流量比、温度比对叶片表面温度分布及冷却效率的影响规律,结果表明叶片前缘、靠近端壁区域温度较高,且压力面0.2倍弧长位置冷却效率最高,吸力面0.4倍弧长附近及压力面尾缘冷却效率较低,相较于温度比,流量比对冷却效率影响更大,温度比保持1.7不变,流量比从0.02增大至0.08时,平均冷却效率从0.30增大至0.71,且在流量比达到0.06时进入平均冷却效率值提升瓶颈;流量比保持0.08不变,温度比从1.56增大至2.36时,平均冷却效率从0.72下降至0.68。

    Abstract:

    This work presents a new light field multispectral radiation thermometry technique and apply it to accurately validate the design effectiveness of a composite cooling structure for aero-engine turbine blades. This temperature measurement method integrates multispectral radiation thermometry with light field imaging technology: by coupling an optical filter array with a light field camera, it enables synchronous acquisition of multi-band radiation information via a single snapshot. Combined with an intelligent optimized temperature inversion algorithm, it effectively minimizes measurement errors induced by emissivity assumptions and background radiation. Compared with the traditional discrete-point measurement method of embedding thermocouples, this method can accurately obtain the two-dimensional temperature field distribution of the blade, with a temperature measurement deviation of no more than 0.33% in the absence of cooling air. Experiments were performed under a mainstream gas temperature of 823 K to obtain the influence laws of flow ratio and temperature ratio on the blade surface temperature distribution and cooling efficiency. The results indicate that higher temperatures are concentrated at the blade leading edge and regions adjacent to the endwalls; the cooling efficiency reaches its peak at the position of 0.2 times the arc length on the pressure surface, while the regions near 0.4 times the arc length on the suction surface and the trailing edge of the pressure surface exhibit relatively low cooling efficiency. The flow ratio exerts a more significant influence on cooling efficiency than the temperature ratio: when the temperature ratio is maintained constant at 1.7, the average cooling efficiency increases from 0.30 to 0.71 as the flow ratio rises from 0.02 to 0.08, and the improvement in average cooling efficiency enters a bottleneck when the flow ratio exceeds 0.06. When the flow ratio is fixed at 0.08, the average cooling efficiency decreases from 0.72 to 0.68 with the temperature ratio increasing from 1.56 to 2.36.

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  • 收稿日期:2025-09-16
  • 最后修改日期:2025-11-26
  • 录用日期:2026-01-26
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