航空学报 > 2011, Vol. 32 Issue (10): 1945-1950   doi: CNKI:11-1929/V.20110526.1756.020

带补偿加热的GH4169间的接触热导测试研究

王宗仁, 张卫方, 唐庆云, 刘升旺   

  1. 北京航空航天大学 可靠性与系统工程学院, 北京 100191
  • 收稿日期:2011-03-07 修回日期:2011-03-28 出版日期:2011-10-25 发布日期:2011-10-27
  • 通讯作者: Tel: 010-82315759 E-mail: weifangzhang831@sohu.com E-mail:weifangzhang831@sohu.com
  • 作者简介:王宗仁(1986- ) 男,博士研究生。主要研究方向:高温合金、材料损伤与性能表征。 Tel: 010-82317968 E-mail: wangzongren12@163.com; 张卫方(1971- ) 男,博士,教授,博士生导师。主要研究方向:材料与性能表征、结构可靠性、高温合金。 Tel: 010-82315759 E-mail: weifangzhang831@sohu.com; 唐庆云(1988- ) 男,博士研究生。主要研究方向:材料损伤与性能表征、故障机理。 Tel: 010-82317968 E-mail: tangqingyunene@163.com; 刘升旺(1986- ) 男,硕士研究生。主要研究方向:纤维增强树脂基复合材料。 Tel: 010-82317968 E-mail: countterrorists@sina.com

Experimental Investigation of Thermal Contact Conductance Across GH4169/GH4169 Interface with Compensation Heater

WANG Zongren, ZHANG Weifang, TABG Qingyun, LIU Shengwang   

  1. School of Reliability and Systems Engineering, Beihang University, Beijing 100191, China
  • Received:2011-03-07 Revised:2011-03-28 Online:2011-10-25 Published:2011-10-27

摘要: 针对航空发动机热端部件的材料特性和工作环境特点,自主研制了带有补偿加热装置的高温、高压接触热导(TCC)测试系统。设计使用纯铜作为热流计材料,使其对于热导率不明确或随温度变化较大的高温合金同样具有较好的适用性。针对航空发动机热端部件常用结构材料GH4169/GH4169在不同界面压力(60~180 MPa)和不同界面温度(150~500 ℃)下的接触热导进行了试验研究。研究结果表明采用该系统进行高温、高压条件下的接触热导试验研究是可行的,利用该测试系统得到了GH4169间的接触热导的变化规律,并分析比较了有、无补偿加热装置条件下的接触热导变化情况。

关键词: 温度补偿, 航空发动机, 高温合金, 接触热导, 接触热阻

Abstract: An experimental setup of high-temperature and high-pressure thermal contact conductance (TCC) with a compensation heater is independently developed according to the material properties and working environments of aero-engine hot-end components. A pure Cu bar is used as the heat-flow meter to measure the axial heat flux, which is also suitable for superalloys whose thermal conductivity is either unclear or exhibits great variation with temperature. An experimental investigation of TCC is conducted with pressed pairs of aero-engine hot-end component structure material GH4169/GH4169 contacts in the range of 150-500 ℃ and 60-180 MPa. The results show that the present experimental setup is feasible for the experimental investigation of high-temperature and high-pressure TCC, and the variation of the TCC across GH4169/GH4169 is obtained. Moreover, the variation of the TCC with and without a compensation heater is studied. The research results may serve as a significant reference for the prediction of aer-oengine thermal properties.

Key words: temperature compensation, aero-engine, superalloy, thermal contact conductance, thermal contact resistance

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