单晶涡轮叶片典型任务循环蠕变分析

石多奇; 张雨曼; 隋天校; 杨晓光

doi:10.13224/j.cnki.jasp.20210702

单晶涡轮叶片典型任务循环蠕变分析

doi: 10.13224/j.cnki.jasp.20210702

北京航空航天大学能源与动力工程学院，北京 100191

基金项目: 国家科技重大专项（2017-Ⅳ-0012-0049）

详细信息

作者简介:
石多奇（1975-），男，教授，博士，研究方向为航空发动机结构强度与寿命可靠性、高温材料本构关系与破坏理论

中图分类号: V232.4
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出版历程
- 收稿日期: 2021-12-10
- 网络出版日期: 2024-01-25

Creep analysis of single crystal turbine blade under typical mission cycle

School of Energy and Power Engineering，Beihang University，Beijing 100191，China

摘要

摘要:
针对单晶涡轮叶片在发动机典型任务循环下的多工况蠕变计算问题，结合变载条件下的单晶合金蠕变本构模型，开发了用于高温结构蠕变计算的ABAQUS/UMAT用户子程序。对某型单晶涡轮叶片进行了典型任务循环下的蠕变计算，识别出可忽略蠕变损伤的工作状态从而实现了载荷谱简化，分别计算了该涡轮叶片在10000个战斗机飞行循环和40000个运输机飞行循环下的蠕变变形，并进行了蠕变寿命评估。结果显示：计算采用的典型载荷状态中，该叶片在巡航及以下状态产生的损伤较小，进行蠕变计算时可以删除，简化后的蠕变载荷谱与原载荷谱下叶片产生的蠕变变形基本相等；不同飞机任务剖面下涡轮叶片具有不同的蠕变寿命，在采用的战斗机典型飞行循环下，该叶片的蠕变寿命约为运输机飞行循环下的1/14，这与发动机的大功率状态持续时间占比有关。
- 涡轮叶片 /
- 典型任务循环 /
- 蠕变变形 /
- 寿命评估 /
- 变载蠕变模型 /
- UMAT子程序
Abstract:
Considering the multiple working conditions creep calculation of single crystal turbine blade under the typical mission profile of engine, combined with the creep constitutive model of single crystal super-alloy under varying loading, a ABAQUS/UMAT subroutine for creep calculation of high temperature structure was developed. The creep of a single crystal turbine blade under the typical design load spectrum was calculated, and the working state of negligible creep damage was identified, so as to simplify the load spectrum. The creep deformations of the turbine blade under 10000 mission cycles of fighter and 40000 mission cycles of transport aircraft were calculated respectively, and the service life was evaluated. The results showed that, under the typical load states used in the calculation, the creep damage of turbine blade under engine cruise state and below was small, which can be ignored in creep calculation. The creep deformation of turbine blade under the simplified creep load spectrum was basically equal to that under the original load spectrum; turbine blades had different creep life under different aircraft mission profiles. Under the typical mission cycle of fighter used in the calculation, the creep life of the turbine blade was about 1/14 of that of transport aircraft, which was related to the duration of high-power state of the engine.
- turbine blade /
- typical mission cycle /
- creep deformation /
- life assessment /
- creep model under varying loading /
- UMAT subroutine

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图 1 变载蠕变规则

Figure 1. Creep rule under varying load

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图 2 UMAT子程序流程图

Figure 2. Flow chart of UMAT subroutine

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图 3 涡轮叶片有限元模型、最大状态温度场与边界条件

Figure 3. Finite element model, maximum state temperature field and boundary conditions of turbine blade

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图 4 民用发动机典型设计载荷谱^[21]

Figure 4. Typical design load spectrum of a civil engine^[21]

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图 5 涡轮叶片等效蠕变应变分布（N=500）

Figure 5. Equivalent creep strain distribution of turbine blade（N = 500）

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图 6 涡轮叶片蠕变损伤分布（N=500）

Figure 6. Creep damage distribution of turbine blade （N=500）

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图 7 不同循环最大状态下涡轮叶片等效应力分布

Figure 7. Equivalent stress distribution of turbine blade under maximum state of different cycles

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图 8 Hill等效应力变化曲线

Figure 8. Variation curve of Hill equivalent stress

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图 9 叶尖截面蠕变伸长量随循环数的变化曲线

Figure 9. Variation curve of tip section creep elongation with cycle

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图 10 各载荷状态占比情况

Figure 10. Proportion of each load state

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图 11 简化蠕变载荷谱

Figure 11. Simplified creep load spectrum

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图 12 叶尖最大径向位移量随循环数的变化曲线

Figure 12. Variation curve of maximum radial displacement of blade tip with cycle

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图 13 不同机型发动机的简化蠕变载荷谱

Figure 13. Simplified creep load spectrums of different aircraft engines

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图 14 涡轮叶片最大蠕变伸长量随循环数的变化曲线

Figure 14. Variation curve of maximum creep elongation of turbine blade with cycle

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表 1 国产某单晶高温合金DDXX蠕变模型参数

Table 1. Creep model parameters of a domestic single crystal superalloy DDXX

T/K	A/10⁻¹⁵	m	n	B	k	r	M₄₄
1033	8.52	4.92	0.3339	1320	3.02	13.5	2.51
1173	34.4	4.64	0.6550	1160	2.32	6.8	2.38
1273	310	4.46	0.8851	717	2.02	5.9	1.85

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表 2 某战斗机典型任务剖面^[22]

Table 2. Typical mission profile of a fighter^[22]

任务段	发动机状态	持续时间/min	占任务总时间比/%
滑行	地面慢车	0.2	0.57
起飞	最大	1	2.83
爬升	额定	4.79	13.57
出航	巡航	3.41	9.66
机动	最大	6.29	17.82
巡航	巡航	8.78	24.87
下降	空中慢车	10.23	28.98
着陆	最大	0.1	0.28
滑行	地面慢车	0.5	1.42

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表 3 某运输机典型任务剖面^[22]

Table 3. Typical mission profile of a transport aircraft^[22]

任务段	发动机状态	持续时间/min	占任务总时间比/%
滑行	地面慢车	0.2	0.20
起飞	最大	1	0.98
爬升	额定	24.2	23.77
巡航	巡航	53.7	52.75
下降	空中慢车	22.1	21.71
着陆	最大	0.1	0.10
滑行	地面慢车	0.5	0.49

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表 4 涡轮叶片蠕变寿命

Table 4. Creep life of turbine blade

飞机类型	战斗机	运输机
飞行循环数	2472	13431
飞行小时数/h	1599	23573

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