再生冷却推力室热障涂层系统的热结构分析

推进技术 ›› 2018, Vol. 39 ›› Issue (2): 380-387.

再生冷却推力室热障涂层系统的热结构分析

邢昱阳,孙冰,宋佳文

北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191

发布日期:2021-08-15
作者简介:邢昱阳，男，硕士生，研究领域为液体火箭发动机热防护。E-mail: xyy6786@buaa.edu.cn 通讯作者:孙冰，女，博士，教授，博士生导师，研究领域为火箭发动机热防护。

Thermomechanical Analysis of a Regeneratively-Cooled Thrust Chamber with Thermal Barrier Coatings

School of Astronautics，Beihang University，Beijing 100191，China,School of Astronautics，Beihang University，Beijing 100191，China and School of Astronautics，Beihang University，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为了设计和优化适用于液体火箭发动机推力室的热障涂层，应用ANSYS的热-结构分析功能，对再生冷却推力室-热障涂层系统进行了热结构有限元分析，得到在不同涂层覆盖下，推力室壁中的温度场和应变场，并通过对热障涂层中应变场的分析，研究不同涂层发生分层剥落的关键位置以及主要驱动力。结果表明，陶瓷层厚度较大的YSZ+NiCrAlY涂层拥有更优异的性能，使推力室壁在热试阶段的最大应变量减少约36.1%；工作循环中，涂层与推力室壁的接触面上会产生较大的应变量，最终有可能导致涂层剥落失效；粘结层能缓解涂层与推力室壁间的热膨胀系数不匹配，使陶瓷层在热试阶段的最大应变量减少约80%。

关键词: 液体火箭发动机；推力室；再生冷却；热障涂层；有限元法；温度场；应变场

Abstract: To design and optimize the thermal barrier coating (TBC) for LRE thrust chamber， finite element analysis of TBC system in regeneratively-cooled thrust chamber is carried out， by the thermomechanical analysis function in ANSYS. The temperature and strain fields of different coatings are computed. Based on the strain fields， dangerous regions and driving forces leading to failure in TBC are determined. The results show that YSZ coatings with a thick ceramic layer and a NiCrAlY bond layer provide better protection， making the maximum strain in thrust chamber wall 36.1% lower in hot test. The failure position of TBC is located at the interface of coating and thrust chamber wall. Bond layer mitigates the mismatched thermal expansion coefficient between coating and thrust chamber wall， making the maximum strain in ceramic layer 80% lower in hot test.

Key words: Liquid rocket engine；Thrust chamber；Regenerative cooling；Thermal barrier coating；Finite element method；Temperature field；Strain filed

邢昱阳,孙冰,宋佳文. 再生冷却推力室热障涂层系统的热结构分析[J]. 推进技术, 2018, 39(2): 380-387.

XING Yu-yang,SUN Bing,SONG Jia-wen. Thermomechanical Analysis of a Regeneratively-Cooled Thrust Chamber with Thermal Barrier Coatings[J]. Journal of Propulsion Technology, 2018, 39(2): 380-387.

参考文献

[1] Schulz U, Leyens C, Fritscher K, et al. Some Recent Trends in Research and Technology of Advanced Thermal Barrier Coatings [J]. Aerospace Science & Technology, 2003, 7(1): 73-80.
[2] Greuel D, Haidn O, Fritscher K. Thermal Barrier Coating for Cryogenic Rocket Engines[C].Indianapolis: AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2002.
[3] Schloesser J, Fedorova T, B?ker M, et al. Thermal Barrier Coatings on Copper Substrates for Rocket Applications[J]. Journal of Solid Mechanics & Materials Engineering, 2010, 4(2): 189-195.
[4] Greuel D, Haidn O, Fritscher K. Thermal Barrier Coating for Cryogenic Rocket Engines[C]. Indianapolis: AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2002.
[5] Sarikaya O, Islamoglu Y, Celik E. Finite Element Modeling of the Effect of the Ceramic Coatings on Heat Transfer Characteristics in Thermal Barrier Applications[J]. Materials & Design, 2005, 26(4): 357-362.
[6] Ranjbarfar M, Absi J, Mariaux G, et al. Modeling of the Residual Stresses and Their Effects on the TBC System after Thermal Cycling Using Finite Element Method[J]. Polskie Towarzystwo Ceramiczne, 2010, 62(3):275-279.
[7] 张津, 吴护林. 发动机喷管隔热涂层的设计和模拟计算[J]. 兵工学报, 2002, 23(2): 209-211.
[8] 孙冰, 宋佳文. 液体火箭发动机推力室壁瞬态加载三维热结构分析[J]. 推进技术, 2016, 37(7): 1328-1333. (SUN Bing, SONG Jia-wen. Three Dimensional Transient Loading Thermomechanical Analysis of LRE Thrust Chamber Wall[J]. Journal of Propulsion Technology, 2016, 37(7): 1328-1333.)
[9] 康玉东, 孙冰. 液体火箭发动机推力室可重复使用技术[J]. 航空动力学报, 2012, 27(7): 1659-1664.
[10] 周宏明, 易丹青, 余志明, 等. 热障涂层的研究现状与发展方向[J]. 材料导报, 2006, 20(3): 4-8.
[11] 张天佑, 吴超, 熊征, 等. 热障涂层材料及其制备技术的研究进展[J]. 激光与光电子学进展, 2014, (3): 27-32.
[12] 蔡国飙, 李家文, 田爱梅, 等. 液体火箭发动机设计[M]. 北京:北京航空航天大学出版社, 2011: 145-147.
[13] Nayebpashaee N, Seyedein S H, Aboutalebi M R, et al.Finite Element Simulation of Residual Stress and Failure Mechanism in Plasma Sprayed Thermal Barrier Coatings Using Actual Microstructure as the Representative Volume[J]. Surface & Coatings Technology, 2016, 291:103-114.
[14] Sláme[c]ka K, Skalka P, Pokluda J, et al. Finite Element Simulation of Stresses in a Plasma Sprayed Thermal Barrier Coating with an Irregular Top-Coat/Bond-coat Interface[J]. Surface & Coatings Technology, 2016, 304: 574-583.
[15] 康玉东, 孙冰. 液体火箭发动机推力室内壁三维热强度分析[J]. 推进技术, 2012, 33(5): 809-813. (KANG Yu-dong, SUN Bing. Three Dimensional Thermomechanical Analysis of Liquid Rocket Engine Thrust Chamber Inner Wall[J]. Journal of Propulsion Technology, 2012, 33 (5): 809-813.)
[16] Zhu J G, Wei C, Xie H M. Simulation of Residual Stresses and Their Effects on Thermal Barrier Coating Systems Using Finite Element Method[J]. Science China Physics Mechanics & Astronomy, 2015, 58(3): 1-10.
[17] 刘纯波, 林锋, 蒋显亮. 热障涂层的研究现状与发展趋势[J]. 中国有色金属学报, 2007, 17(1): 1-13.　　　　　　　　　　　　　*　收稿日期:2016-11-29；修订日期:2017-02-18。作者简介:邢昱阳,男,硕士生,研究领域为液体火箭发动机热防护。E-mail: xyy6786@buaa.edu.cn通讯作者:孙冰,女,博士,教授,博士生导师,研究领域为火箭发动机热防护。E-mail: sunbing@buaa.edu.cn(编辑:史亚红)