航空发动机测温晶体的退火特性研究  

Research on Crystals Annealing Characteristic for Areoengine Temperature Measurement

作　　者：张兴[1] 张志学[1] 薛秀生[1] 张羽鹏[1] 赵迎松[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2013年第4期72-77,88,共7页Aeroengine

摘　　要：针对航空发动机关键构件高温测试的技术难题,研究了1种用晶体作为传感器的测温技术,阐述了晶体的退火特性和缺陷观察方法,利用X射线衍射(XRD)研究中子辐照SiC晶体的退火特性,发现辐照后晶体的XRD峰的半高宽(Full Width at Half Maximum,FWHM)增大,又随退火温度的升高,在700～1230℃呈线性规律的回复。基于此发展了1种适合测量高温和复杂温度场的技术方法。采用添加K2CO3的KOH为腐蚀剂,对辐照前、后以及辐照后退火的SiC单晶进行位错腐蚀观察,结果表明:经中子辐照的晶体中位错面积比随退火温度的变化趋势与FWHM的变化趋势基本一致,由此认为经中子辐照所产生的位错可能是导致XRD峰的FWHM变化的1个重要因素。Aiming at the technology difficulty of high temperature measurement of areoengine key component, a new thermometry using crystals as sensors was studied. The crystal annealing characteristic and the method of observing defects were described. The annealing characteristic of SiC crystals was analyzed by X-Ray Diffraction （XRD）. It was found that post-irradiation the Full Width at Half Maximum （FWHM） of the XRD peaks was increased and with increasing of the annealing temperature a linear law recovery was shown at the range of 700-1230 ℃. A novel temperature measurement technique for the measuring of high temperature and complicated temperature field were developed based on the law. Moreover, the dislocation erosion for the irradiation, post-irradiation SiC crystals anneal were investigated using KOH added K2CO3 as a chemical etchant. The results show that the change trends of dislocation area ratio in neutron irradiated with the annealing temperature is agreed with that of FWHM. The dislocations induced by neutron irradiation could be one of important factors for the changes of FWHM of XRD peaks.

关 键 词：测温 晶体 退火 缺陷 半高宽 航空发动机 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]