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首页> 外文期刊>High temperature materials and processes >High Temperature Mechanical Properties of Thermal Barrier Coated Superalloy Applied to Combustor Liner of Aero Engines
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High Temperature Mechanical Properties of Thermal Barrier Coated Superalloy Applied to Combustor Liner of Aero Engines

机译：航空发动机燃烧室衬里热障涂层高温合金的高温力学性能

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摘要

High temperature load controlled fatigue, hot tensile and accelerated creep properties of thermal barrier coated (TBC) Superni C263 alloy used as a candidate material in combustor liner of aero engines are highlighted in this paper. Acoustic emission technique has been utilised to characterise the ductile-brittle transition temperature of the bond coat. Results revealed that the DBTT (ductile to brittle transition temperature) of this bond coat is around 923 K, which is in close proximity to the value reported for CoCrAlY type of bond coat. Finite element technique, used for analysing the equivalent stresses in the bond coat well within the elastic limit, revealed the highest order of equivalent stress at 1073 K as the bond coat is ductile above 923 K. The endurance limit in fatigue and the life of TBC coated composite under accelerated creep conditions are substantially higher than those of the substrate material. Fractographic features at high stresses under fatigue showed intergranular cleavage whereas those at low stresses were transgranular and ductile in nature. Delamination of the bond coat and spallation of the TBC at high stresses during fatigue was evident. Unlike in the case of fatigue, the mode of fracture in the substrate' at very high stresses was transgranular whereas that at low stresses was intergranular in creep.
机译：本文重点介绍了热障涂层（TBC）Superni C263合金的高温负荷控制疲劳，热拉伸和加速蠕变性能，该合金用作航空发动机燃烧室衬套的候选材料。声发射技术已被用来表征粘结涂层的韧性-脆性转变温度。结果表明，该粘结层的DBTT（韧性至脆性转变温度）约为923 K，与报道的CoCrAlY型粘结层的值非常接近。用于分析粘结层等效应力的弹性有限元技术，揭示了当粘结层在923 K以上时具有延展性时，等效应力的最高阶为1073K。疲劳极限和TBC寿命在加速蠕变条件下涂覆的复合材料明显高于基材。在疲劳下处于高应力下的分形特征表现出晶间分裂，而在低应力下的分形特征本质上是穿晶的和延性的。疲劳期间在高应力下，粘结层分层和TBC剥落是明显的。与疲劳情况不同，在非常高的应力下，基体的断裂模式是穿晶的，而在低应力下，其蠕变是晶间的。

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