涡轮导向叶片综合冷却特性实验研究

推进技术 ›› 2018, Vol. 39 ›› Issue (12): 2772-2778.

涡轮导向叶片综合冷却特性实验研究

李广超,莫唯书,张魏,赵长宇,黄福幸

沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室，辽宁沈阳 110136,沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室，辽宁沈阳 110136,沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室，辽宁沈阳 110136,沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室，辽宁沈阳 110136,沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室，辽宁沈阳 110136

发布日期:2021-08-15
基金资助:
国家自然科学基金(51406124)；辽宁省自然科学基金(201602576)。

Experimental Investigation on Integrated Cooling Performance of Nozzle Guide Vane

Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System，Shenyang Aerospace University，Shenyang 110136，China,Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System，Shenyang Aerospace University，Shenyang 110136，China,Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System，Shenyang Aerospace University，Shenyang 110136，China,Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System，Shenyang Aerospace University，Shenyang 110136，China and Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System，Shenyang Aerospace University，Shenyang 110136，China

Published:2021-08-15

摘要/Abstract

摘要： 为了优化设计涡轮导向叶片冷气用量，采用红外测温技术对叶栅进出口压比2.378，冷热流体流量比0.059～0.118的叶片综合冷却效果进行了研究，获得了叶片表面综合冷却效果二维分布以及展向平均和区域平均综合冷却效果随流量比的变化规律。结果表明:流量比变化对前缘和压力面区域平均综合冷却效果的影响明显大于吸力面。前缘最大展向平均综合冷却效果出现在滞止线附近，该冷却结构对前缘可以进行有效冷却。流量比由0.059增大到0.118，区域平均综合冷却效果先升高后降低，流量比0.078获得最大综合冷却效果。将设计点流量比从0.098减小到0.078，不仅减少冷气用量，还提高了叶片综合冷却效果。

关键词: 综合冷却效果；涡轮；红外测温；流量比

Abstract: In order to optimize the mass flow rate of coolant， integrated cooling performance of nozzle guide vane was studied by infrared temperature measurement method at cascade pressure ratio of 2.378 and mass flow ratios of 0.059～0.118. The two dimensional distributions of integrated cooling efficiency on the nozzle guide vane and the spanwise averaged and the surface averaged integrated cooling efficiency were obtained with the variation of mass flow ratios. The results show that influence of mass flow ratios on the integrated cooling efficiency of leading edge and pressure side is significant compared to the case of the suction side. The largest value of the spanwise averaged integrated cooling efficiency appear near the stagnation line of the leading edge. It implies that the cooling structure has an effective cooling on the leading edge. The surface averaged integrated cooling efficiency increases firstly and then decreases when the mass flow ratios increase from 0.059 to 0.118. The largest integrated cooling efficiency appears at mass flow ratio of 0.078. If the mass flow ratio in running condition decreases from 0.098 to 0.078， the coolant will be reduced and meanwhile the integrated cooling efficiency will be raised.

Key words: Integrated cooling efficiency；Turbine；Infrared temperature measurement；Mass flow ratio

李广超,莫唯书,张魏,赵长宇,黄福幸. 涡轮导向叶片综合冷却特性实验研究[J]. 推进技术, 2018, 39(12): 2772-2778.

LI Guang-chao,MO Wei-shu,ZHANG Wei,ZHAO Chang-yu,HUANG Fu-xing. Experimental Investigation on Integrated Cooling Performance of Nozzle Guide Vane[J]. Journal of Propulsion Technology, 2018, 39(12): 2772-2778.

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