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Oxidation behaviour of LM 6000 gas turbine engine substrate cobalt-base alloy 188

机译:LM 6000燃气轮机发动机基底钴基合金188的氧化行为

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摘要

The oxidation of multi-component alloys is complex and there are several competing oxidation reactions. This paper focuses on the oxidation performance of a gas turbine engine substrate, alloy 188. Co-Ni-Cr-W alloys can have a complex oxide structure that varies as a function of time and temperature. Alloy 188 was exposed in air at temperatures from 1050 to 1200 deg C for up to 1500 h to determine its oxidation kinetics and to elucidate the form of damage accumulation. Previous results show parabolic corrosion kinetics at low (820 deg C) temperatures and this work found similar kinetics above 1150 deg C. However, in the mid temperature range, 1050-1100 deg C, linear kinetics were observed. The performance of alloy 188 is of interest because of its use in turbines with oxidation resistant coatings designed to allow higher temperature operation than would normally be recommended. Because of the differing kinetics the lower temperature exposures give higher material loss than the higher temperature exposures at 1150 deg C after 1500 h. Rates of damage accumulation at 1050 deg C were of the order of 10 mu m/h.
机译:多组分合金的氧化非常复杂,并且存在几种竞争的氧化反应。本文着重于燃气轮机发动机基体188的氧化性能。Co-Ni-Cr-W合金可具有随时间和温度变化的复杂氧化物结构。合金188在1050至1200摄氏度的温度下暴露于空气中长达1500小时,以确定其氧化动力学并阐明损伤累积的形式。先前的结果显示了在低温(820摄氏度)下的抛物线腐蚀动力学,这项工作在1150摄氏度以上发现了相似的动力学。但是,在中间温度范围(1050至1100摄氏度),观察到了线性动力学。合金188的性能之所以令人关注,是因为它用于具有抗氧化涂层的涡轮机中,该涂层设计用于允许比通常建议的高温运行。由于动力学不同,与1500 h后1150℃的较高温度暴露相比,较低的温度暴露产生更高的材料损失。 1050℃下的损伤积累速率约为10μm/ h。

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