航天推进技术研究院主办
[1]王 凯,张 静,刘进涛,等.GH4586合金涡轮盘预制坯优化与组织均匀性控制[J].火箭推进,2021,47(01):83-89.
WANG Kai,ZHANG Jing,LIU Jintao,et al.Preformed blank optimization and microstructure uniformity control of GH4586 alloy turbine disk[J].Journal of Rocket Propulsion,2021,47(01):83-89.
点击复制
WANG Kai,ZHANG Jing,LIU Jintao,et al.Preformed blank optimization and microstructure uniformity control of GH4586 alloy turbine disk[J].Journal of Rocket Propulsion,2021,47(01):83-89.
GH4586合金涡轮盘预制坯优化与组织均匀性控制
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
47
期数:
2021年01期
页码:
83-89
栏目:
工艺与材料
出版日期:
2021-02-28
- Title:
- Preformed blank optimization and microstructure uniformity control of GH4586 alloy turbine disk
- 文章编号:
- 1672-9374(2021)01-0083-07
- Keywords:
- GH4586 alloy; turbine disk; microstructure uniformity; forging; preformed blank
- 分类号:
- TG113.1; TG316.3
- 文献标志码:
- A
- 摘要:
- GH4586合金涡轮盘是新一代液体火箭发动机的核心部件之一,服役环境极其恶劣,提高涡轮盘模锻件微观组织均匀性有益于提高产品力学性能的稳定性和可靠性。通过热压缩试验,研究了变形温度、应变对GH4586合金微观组织和再结晶行为的影响,得到了GH4586合金热成形工艺参数范围; 结合有限元仿真和模锻成形试验,分析了不同预制坯形状对涡轮盘模锻件应变分布和组织均匀性的影响,采用从边缘到中心梯度升高的双陀螺形预制坯形状、在1 060 ℃条件下进行模锻成形,可以获得组织均匀的涡轮盘模锻件,心部晶粒度等级达到6～7级,盘部R/2处和边缘处晶粒度等级7～8级; 室温、低温和高温力学性能均满足标准要求,特别是-196 ℃时延伸率和600 ℃时抗拉强度相较原工艺方案分别提高了37%和12%。
- Abstract:
- GH4586 alloy turbine disk is one of the core components of the new generation liquid rocket engine.Due to the extremely terrible service environment, it is necessary to improve the microstructure uniformity of turbine disk in die forging and therefore is beneficial to improve the stability and reliability of mechanical properties. The effects of temperature and strain on the microstructures and recrystallization behavior of GH4586 alloy were studied by hot compression tests, and the range of hot forming process parameters were obtained. Based on finite element simulation and die forging experiment, the effects of different preformed blanks on strain distribution and uniformity of microstructure were compared and analyzed. The turbine disk die forging with uniform microstructure was obtained by using the double gyro preform shape with gradient rising from edge to center, and forged at 1 060 ℃. The grain size reached 6～7 at the core, and 7～8 when locating at the middle and edge. The mechanical properties of GH4586 alloy turbine disk made by the preformed blank at room temperature, cryogenic and high temperature all meet the requirement of the standards, especially the elongation at -196 ℃ and the ensile strength at 600 ℃ were increased by 37% and 12% compared with the one made by original scheme,respectively.
参考文献/References:
[1] 崔彤.两种高性能镍基高温合金长期时效后的组织演化与力学行为[D].沈阳: 东北大学,2004.
[2] 任众,朱东华,许开富.多场环境下涡轮盘的强度与振动安全性仿真优化研究[J].火箭推进,2016,42(6):36-42.
REN Z,ZHU D H,XU K F.Multiphysics-based simulation and optimization on strength and vibration security of turbine disk[J].Journal of Rocket Propulsion,2016,42(6):36-42.
[3] 张贵田.高压补燃液氧煤油发动机[M].北京: 国防工业出版社,2005.
[4] 高波,曾凡浩,古一,等.航天发动机用GH4586镍合金表面含镍金属陶瓷涂层的结合与抗氧化性能[J].粉末冶金材料科学与工程,2018,23(5):527-533.
[5] 张海燕,程明,赵忠,等.GH4169合金涡轮盘热模锻中晶粒尺寸演变的数值模拟与分析[J].锻压技术,2017,42(11):1-5.
[6] 王帅.GH4586合金动态再结晶行为及长期时效对其裂纹扩展特性的影响[D].沈阳: 东北大学,2011.
[7] 张北江,赵光普,焦兰英,等.热加工工艺对GH4586合金微观组织的影响[J].金属学报,2005,41(4):351-356.
[8] 胥国华.GH4586合金热加工参数及热处理制度的研究[D].沈阳:东北大学,2004.
[9] 李爱民,王盛安,周一玲,等.GH4586合金的热加工工艺[J].钢铁研究学报,2003,15(S1):383-385.
[10] 魏振华,李铸国,DURAND Camille.不同温度锻压时Inconel 625镍基高温合金的形变量和晶粒尺寸[J].机械工程材料,2019,43(3):67-71.
[11] 高占平.面向锻造过程GH4169涡轮盘晶粒组织均匀性研究[D].秦皇岛: 燕山大学,2015.
[12] 蒋世川.GH4169高温合金热变形行为及组织演变[J].钢铁钒钛,2018,39(2):146-152.
[13] LIU Y H,NING Y Q,YANG X M,et al.Effect of temperature and strain rate on the workability of FGH4096 superalloy in hot deformation[J].Materials & Design,2016,95: 669-676.
[14] FREUND L P,STARK A,PYCZAK F,et al.The grain boundary pinning effect of the μ phase in an advanced polycrystalline γ/γ' co—base superalloy[J].Journal of Alloys and Compounds,2018,753: 333-342.
[15] 钱芳,王忠堂.变形工艺参数对GH4169合金热变形组织演变的影响[J].铸造技术,2018,39(7):1562-1564.
[16] MCQUEEN H J.Development of dynamic recrystallization theory[J].Materials Science and Engineering: A,2004,387/388/389: 203-208.
[17] 吾志岗,李德富,郭胜利,等.变形条件对GH625合金高温变形动态再结晶的影响[J].稀有金属,2010,34(6):833-838.
[18] DU J H,LU X D,DENG Q,et al.Progress in the research and manufacture of GH4169 alloy[J].Journal of Iron and Steel Research,International,2015,22(8):657-663.
[19] DU J H,DENG Q,DONG J X,et al.Recentprogress of manufacturing technologies on C&W superalloys in China[M]//8th International Symposium on Superalloy 718 and Derivatives.Hoboken,NJ,USA: John Wiley & Sons,Inc.,2014: 31-46.
[20] 陈林俊,陈刚,朱强,等.镍基高温合金微型涡轮盘热塑性成形工艺[J].精密成形工程,2018,10(2):25-30.
相似文献/References:
[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.
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(01):13.
[2]杜大华,黄道琼,黄金平,等.火箭发动机涡轮盘模态影响因素与振动安全性分析[J].火箭推进,2021,47(01):21.
DU Dahua,HUANG Daoqiong,HUANG Jinping,et al.Analysis on modal influence factors and vibration safety of rocket engine turbine disk[J].Journal of Rocket Propulsion,2021,47(01):21.
[3]王凯,王东方,刘友强,等.变形高温合金在液体火箭发动机中的应用进展及展望[J].火箭推进,2024,50(01):57.[doi:10.3969/j.issn.1672-9374.2024.01.005]
WANG Kai,WANG Dongfang,LIU Youqiang,et al.Application and prospect of wrought superalloy in liquid rocket engine[J].Journal of Rocket Propulsion,2024,50(01):57.[doi:10.3969/j.issn.1672-9374.2024.01.005]
备注/Memo
收稿日期:2019-12-15
基金项目:装备发展部载人航天领域预先研究项目(05XX02)
作者简介:王凯(1991—),男,硕士,研究领域为火箭发动机金属材料热成形。
更新日期/Last Update:
2021-02-20