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

CHENG Jun-hua; NI Bin; DENG Hong-wu; TIAN Shu-qing; CHEN Hao

doi:10.13224/j.cnki.jasp.2014.08.009

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

更新时间：2026-07-07

- Experimental technique and its validation for heat transfer in cooling channels at high rotation numbers
- Issue 8, (2014)
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.08.009
  CLC：
- Published：2014
- 稿件说明：
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程俊华, 倪彬, 邓宏武, 田淑青, 陈豪. 高旋转数内冷通道换热实验技术及验证[J]. 航空动力学报, 2014, (8): 1817-1823. doi: 10.13224/j.cnki.jasp.2014.08.009

CHENG Jun-hua, NI Bin, DENG Hong-wu, et al. Experimental technique and its validation for heat transfer in cooling channels at high rotation numbers[J]. 2014, (8).
程俊华, 倪彬, 邓宏武, 田淑青, 陈豪. 高旋转数内冷通道换热实验技术及验证[J]. 航空动力学报, 2014, (8): 1817-1823. doi: 10.13224/j.cnki.jasp.2014.08.009 DOI：

CHENG Jun-hua, NI Bin, DENG Hong-wu, et al. Experimental technique and its validation for heat transfer in cooling channels at high rotation numbers[J]. 2014, (8). DOI： 10.13224/j.cnki.jasp.2014.08.009.

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%.

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.

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Related Institution

China Aviation Powerplant Research Institute, Aviation Industry Corporation of China

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南京工程学院能源与动力工程学院

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室

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