【摘要】 航改型燃气轮机因其研制基础好、设计周期短、结构紧凑、燃料适应性强等优点，在海上油气平台、船舶动力及管道输送等领域得到了广泛应用．航改型燃气轮机叶片在高温、高压等苛刻环境下工作时，蠕变是其主要失效方式之一．为确保叶片的运行可靠性，通常选用抗蠕变性能较好的镍基合金作为制造材料．该种材料蠕变第三阶段较为明显，占比较高，当前的蠕变损伤本构方程难以精确表征镍基合金蠕变第三阶段的失效行为．针对上述问题，本文提出了一种可合理描述蠕变第三阶段的损伤本构模型，并得到了不同温度下蠕变实验数据的验证．该模型的提出可为航改型燃气轮机高温部件的寿命精准预测和可靠性设计提供较好的理论基础．更多还原

【Abstract】 Because of its advantages of good development foundation, short design cycle, compact structure and strong fuel adaptability, the aero-derivative gas turbine has been widely used in the field of offshore oil and gas platform, marine power and pipeline transportation, etc. For the aero-derivative gas turbine blades working in high temperature, high pressure and other harsh environments, creep is one of the main failure modes. In order to ensure the operation reliability of the blade, nickel-based alloy with strong creep resistance is usually selected as its constitutive material. The nickel-based alloy has obvious third stage of creep,occupying a relatively high proportion of its whole life. The current creep damage constitutive model is difficult to accurately characterize the failure behavior of the third stage of creep for the nickel-based alloys. In response to the above problem, a creep damage constitutive model which can reasonably describe the third stage of creep of the high temperature materials is proposed in this paper. The model is validated by comparing with the creep experimental data under different temperatures. The proposed model can provide a theoretical guideline for accurate life prediction and reliability design of the high temperature components of aero-derivative gas turbines.更多还原