航天推进技术研究院主办
[1]杜大华,王 珺,王红建,等.液体火箭发动机涡轮盘低周疲劳寿命预测[J].火箭推进,2020,46(06):13-21.
DU Dahua,WANG Jun,WANG Hongjian,et al.Low cycle fatigue life prediction of a liquid rocket engine turbine disk[J].Journal of Rocket Propulsion,2020,46(06):13-21.
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DU Dahua,WANG Jun,WANG Hongjian,et al.Low cycle fatigue life prediction of a liquid rocket engine turbine disk[J].Journal of Rocket Propulsion,2020,46(06):13-21.
液体火箭发动机涡轮盘低周疲劳寿命预测
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
46
期数:
2020年06期
页码:
13-21
栏目:
研究与设计
出版日期:
2020-12-31
- Title:
- Low cycle fatigue life prediction of a liquid rocket engine turbine disk
- 文章编号:
- 1672-9374(2020)06-0013-09
- Keywords:
- fatigue life; low cycle fatigue; turbine disk; liquid rocket engine
- 分类号:
- V434.2
- 文献标志码:
- A
- 摘要:
- 涡轮是液体火箭发动机重要的能量转换部件,其工作可靠性将直接关系到发动机乃至航天运载器的安全性,因此迫切需要对涡轮盘的疲劳寿命进行准确预测。首先,进行涡轮全三维非定常气—热—固耦合分析,给出涡轮启停、稳定工作过程的压力、温度载荷; 其次,在离心力、气动载荷和热负荷共同作用下进行弹塑性分析,获取涡轮在启动、关机瞬变过程及稳定运转阶段应力应变响应数据; 再次,采用Morrow弹性应力线性修正方法进行平均应力修正,利用基于Von-Mises应力修正方法和Manson-McKnight多轴应力方法将多轴应力作用转换为单轴应力作用,并以GH4586材料疲劳性能试验数据为基础,提出一种基于等寿命原理修改应变—寿命预估公式的方法; 最后,基于局部应力应变的修正Manson-Coffin(M—C)通用斜率方程对轮盘热端结构在工作循环下的低周疲劳寿命进行精确分析。研究表明,涡轮盘具有一定的疲劳强度安全裕度,启动过程力热冲击对轮盘疲劳寿命的影响较大,分析结论可为涡轮疲劳强度设计提供参考依据。
- Abstract:
- Turbine is an important energy conversion component of liquid rocket engine, whose working reliability will be directly related to the safety of engine and even space vehicle.Therefore, it is urgent to accurately predict the fatigue life of turbine disk.First, a full three-dimensional unsteady gas-heat-solid coupling analysis of turbine was carried out, and the pressure and temperature loads of turbine during start-stop and stable operating were present.Then, the elastic-plastic analysis was performed under the combined action of centrifugal force, aerodynamic load and thermal load, so the stress-strain response data of turbine disk during the startup and shutdown transient processes and the stable operating stage was obtained.Thirdly, the Morrow elastic stress linear correction method for average stress correction was adopted.The Von-Mises stress correction method and the Manson-McKnight multi-axial stress method were used to convert the multi-axial stress effect into a uniaxial stress effect.Based on the fatigue performance test data of GH4586, a method for modifying the strain-life prediction formula based on the principle of equal life was proposed.Finally, based on the modified Manson-Coffin(M-C)general slope equation of local stress-strain, the low cycle fatigue(LCF)life of the hot end structure of disk under working cycle was predicted accurately.The research shows that, the turbine disk has a certain safety margin of fatigue strength, the impact of force and thermal shock on fatigue life of disk is greater during the startup process, and the conclusions can also provide a reference for the fatigue strength design of turbine.
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备注/Memo
收稿日期:2020-03-25; 修回日期:2020-05-15 基金项目:液体火箭发动机技术重点实验室基金项目(HTKJ2020KL011007); 陕西省创新能力支撑计划项目(18JK0813) 作者简介:杜大华(1977—),男,博士,研究员,研究领域为结构强度、振动与可靠性
更新日期/Last Update:
1900-01-01