高旋转数内冷通道换热实验技术及验证

程俊华; 倪彬; 邓宏武; 田淑青; 陈豪

doi:10.13224/j.cnki.jasp.2014.08.009

高旋转数内冷通道换热实验技术及验证

doi: 10.13224/j.cnki.jasp.2014.08.009

1. 北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室, 北京 100191;
2. 中国航空工业集团公司商用航空发动机有限责任公司设计研发中心, 上海 201108

详细信息

作者简介:
程俊华（1988-），男，河南周口人，硕士生，主要从事旋转换热研究。

中图分类号: V235.1
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出版历程
- 收稿日期: 2013-05-13
- 刊出日期: 2014-08-28

Experimental technique and its validation for heat transfer in cooling channels at high rotation numbers

1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Research and Development Center, Commercial Aircraft Engine Company Limited, Aviation Industry Corporation of China, Shanghai 201108, China

摘要

摘要: 通过内冷通道换热理论分析及实验系统优化，获得了使内冷通道内气体压力保持在500kPa以上的高旋转数实验技术.旋转数和雷诺数的范围分别为0~2.08，10⁴~7×10⁴，极大满足了旋转数与雷诺数同时覆盖真实发动机涡轮叶片工作参数的实验需求.证实了雷诺数和旋转数对内冷通道换热的影响可以解耦.而应用该实验技术进行同等旋转数实验时，内冷通道热损失占总加热量的比例和实验误差分别降低到18%和±10%.
- 高压 /
- 高雷诺数 /
- 高旋转数 /
- 对流换热 /
- 内冷通道 /
- 实验技术
Abstract: Based on analysis of cooling channel heat transfer theory and test system optimization, an experimental technology at high rotation numbers with gas pressure in cooling channel higher than 500kPa was developed and implemented. The rotation number and Reynolds number ranged from 0 to 2.08 and 10⁴ to 7×10⁴, respectively, which covered the work parameters of real engine turbine blade. It is found that the effects of Reynolds number and rotation number on heat transfers in cooling channel are able to be separated. Under the condition of the same rotation number, the ratio of cooling channel heat loss and total heat and test error can be reduced to 18% and ±10% respectively in this scenario.
- high pressure /
- high Reynolds number /
- high rotation number /
- convective heat transfer /
- cooling channel /
- experimental technique

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参考文献(15)

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