宇航材料工艺
宇航材料工藝
우항재료공예
AEROSPACE MATERIALS & TECHNOLOGY
2010年
2期
28-32,36
,共6页
抗热震性能%ZrB%裂纹%残余强度
抗熱震性能%ZrB%裂紋%殘餘彊度
항열진성능%ZrB%렬문%잔여강도
Thermal shock resistance%ZrB_2%Cracking%Residual strength
通过水淬法对原位合成与热压烧结制备的组分为ZrB_2-20%(体积分数,下同)SiC-6.05%ZrC陶瓷材料的热震性能进行了研究.对比了不同热震温差、室温水(25℃)与沸水冷却环境、单次与五次循环热震次数以及高温氧化对原位合成试样抗热震性能的影响.计算了原位合成与热压烧结两种工艺制备的同组分试样的抗热震参数,结合试验结果探讨了材料的抗热震机理.结果表明,原位合成试样的抗热震性能优于热压烧结试样.
通過水淬法對原位閤成與熱壓燒結製備的組分為ZrB_2-20%(體積分數,下同)SiC-6.05%ZrC陶瓷材料的熱震性能進行瞭研究.對比瞭不同熱震溫差、室溫水(25℃)與沸水冷卻環境、單次與五次循環熱震次數以及高溫氧化對原位閤成試樣抗熱震性能的影響.計算瞭原位閤成與熱壓燒結兩種工藝製備的同組分試樣的抗熱震參數,結閤試驗結果探討瞭材料的抗熱震機理.結果錶明,原位閤成試樣的抗熱震性能優于熱壓燒結試樣.
통과수쉬법대원위합성여열압소결제비적조분위ZrB_2-20%(체적분수,하동)SiC-6.05%ZrC도자재료적열진성능진행료연구.대비료불동열진온차、실온수(25℃)여비수냉각배경、단차여오차순배열진차수이급고온양화대원위합성시양항열진성능적영향.계산료원위합성여열압소결량충공예제비적동조분시양적항열진삼수,결합시험결과탐토료재료적항열진궤리.결과표명,원위합성시양적항열진성능우우열압소결시양.
The thermal shock behavior of ZrB_2-20% SiC -6.05% ZrC composites fabricated with in-situ method and hot-pressing was studied by means of quenching into water from high temperatures. The effects of thermal shock temperature differences, cool (25 ℃ of bath temperature) and boiling water as cooling medium, single and five cyclic shocks and high temperature oxidation on thermal shock resistance of samples fabricated through in-situ method were investigated. The thermal shock resistance parameters of samples fabricated through in-situ method and hot pressing were compared and then the mechanism of thermal shock resistance was also discussed. The results show that thermal shock property of in-situ sample was better than that of hot-pressing sample.