冷却流道布局对铣槽喷管低周疲劳寿命的影响

推进技术 ›› 2013, Vol. 34 ›› Issue (9): 1257-1265.

冷却流道布局对铣槽喷管低周疲劳寿命的影响

程诚,王一白,刘宇,刘达伟,李波

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;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:程诚(1987—),男,博士生,研究领域为可重复使用火箭发动机技术等。E-mail:ccheng.buaa@gmail.com

Effects of Coolant Passage Layout on Low Cycle Fatigue Life of Milled Channel Nozzle

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究不同的冷却流道布局对大面积比铣槽喷管三维再生冷却槽道在循环工作条件下的热结构响应和低周疲劳寿命的影响, 采用有限体积流—热耦合计算方法、非线性有限元热—结构耦合分析方法和局部应变法对比分析了冷却剂单向逆流、单向顺流和先顺向流动再逆向流动的来回流三种流道布局方案。计算结果表明,铣槽喷管内衬最严重的节点应变主要发生在喷管前部内衬燃气侧壁面与肋条对称面及槽道对称面相交的危险区域,这也是节点低周疲劳寿命最小的位置；铣槽内衬节点的应变时间历程主要由塑性应变决定,肋条与槽道对称面上内衬节点的热结构响应存在较大差异；采用冷却剂单向逆流布局的铣槽喷管内衬节点应变幅和残余应变最大,导致喷管疲劳使用寿命最短；采用冷却剂单向顺流布局的铣槽喷管内衬节点应变幅和残余应变最小,导致喷管低周疲劳寿命最长；采用冷却剂来回流布局的再生冷却喷管铣槽内衬的热结构响应和疲劳使用寿命均处于上述两者之间,但取消了喷管尾部集合器和外置冷却剂供给管路等易失效的部件。 

关键词: 再生冷却喷管;冷却剂流道;低周疲劳寿命;非线性有限元;热结构耦合 

Abstract: To investigate the effects of different coolant passage layouts on the thermal-structural response and low cycle fatigue life of 3D regeneratively cooled channel wall nozzle with high area ratio under cyclic working loads, the finite volume fluid-thermal coupling calculation method, nonlinear finite element thermal-structural coupling analysis method and local strain method were adopted to analyze the coolant backward flow layout, coolant forward flow layout and coolant forward to backward flow layout. Numerical simulation results show that the most serious strain on milled liner of channel wall nozzle mainly occurs at the intersectant regions of liner gas side wall and symmetric planes of rib and channel in the front of nozzle extension, where the minimum node low cycle fatigue life takes place. The node strain history of milled channel nozzle is primarily dominated by the plastic deformation, and the thermal-structural responses between liner nodes, respectively, locating on the symmetric planes of rib and channel exist significant difference. The largest strain amplitude and residual strain during cyclic operation of milled channel nozzle employing coolant backward flow layout result in the shortest fatigue service life. On the contrary, the milled channel nozzle employing coolant forward flow layout with the smallest strain amplitude and residual strain has the longest low cycle fatigue life. Both the thermal-structural response and fatigue life of milled channel nozzle employing coolant forward to backward flow layout fall in between above two nozzles, but it has eliminated the easily damaged aft manifold and coolant feed line. 

Key words: Regeneratively cooled nozzle; Coolant passage; Low cycle fatigue life; Nonlinear finite element; Thermal-structural coupling

程诚,王一白,刘宇,刘达伟,李波. 冷却流道布局对铣槽喷管低周疲劳寿命的影响[J]. 推进技术, 2013, 34(9): 1257-1265.

CHENG Cheng, WANG Yi-bai, LIU Yu, LIU Da-wei, LI Bo. Effects of Coolant Passage Layout on Low Cycle Fatigue Life of Milled Channel Nozzle[J]. Journal of Propulsion Technology, 2013, 34(9): 1257-1265.

参考文献

[1] Komar D R,Christenson R L.Reusable Launch Vehicle Engine Systems Operations Analysis[R].AIAA 96-4246.
[2] Marsik S J,Gawrylowicz H T.Structural Integrity and Durability for Space Shuttle Main Engine and Future Reusable Space Propulsion Systems[R].AIAA 86-1513.
[3] Jeffry F, Fritz K,Frank S.Development of Channel Wall Nozzles for Use on Liquid Propellant Rocket Engine[R].AIAA 2005-4306.
[4] In-Kyung S,William A.A Subscale-Based Rocket Combustor Life Prediction Methodology[R].AIAA 2005-3570.
[5] 杨进慧, 陈涛, 金平,等.液体火箭发动机再生冷却槽寿命预估[J].航空动力学报, 2012,2(4):907-912.
[6] Jorg R R, Oskar J H,Evgeny B Z.Influence of Time Dependent Effects on the Estimated Life Time of Liquid Rocket Combustion Chamber Walls[R].AIAA 2004-3670.
[7] Cikanek H A.Characteristics of Space Shuttle Main Engine Failures[R].AIAA 87-1939.
[8] Larson E W.Investigation of the Fuel Feed Line Failures on the Space Shuttle Main Engine[R].AIAA 80-1309.
[9] Winterfeldt L,Stenstrom E.Functional Aspects on Laser Welded Sandwich Walls for Rocket Engine Nozzles[R].AIAA 2001-3695.
[10] Boman A,Haggander J.Laser Welded Channel Wall Nozzle Design, Manufacturing and Hot Gas Testing[R].AIAA 99-2750.
[11] Vinod K A, Steven M A.Viscoplastic Analysis of an Experimental Cylindrical Thrust Chamber Liner[J].AIAA Journal, 1992,0(3):781-789.
[12] Jorg R R, Malte R H,Oskar J H.Optimization of Geometric Parameters of Cryogenic Liquid Rocket Combustion Chambers[R].AIAA 2001-3408.
[13] Weiss J M,Smith W A.Preconditioning Applied to Variable and Constant Density Flows[J].AIAA Journal, 1995,3(11):2050-2057.
[14] 高薪蕙, 邓忠民, 王静涛.TEC结构的三维非线性瞬态温度场分析[J].计算力学学报, 2012,9(1):25-30.
[15] John J E,Ronald F Z.Thrust Chamber Life Prediction:Volume 1, Mechanical and Physical Properties of High Performance Rocket Nozzle Materials[R].NASA CR-134806,5.
[16] In-Kyung Sung.Fatigue Life Prediction of Liquid Rocket Engine Combustor with Subscale Test Verification[D].West Lafayette:Purdue University, 2006.
[17] Miner M A.Cumulative Damage in Fatigue[J].Journal of Applied Mechanics, 1945,6(7):159-164.
[18] Manson S S,Halford G.A Method of Estimating High Temperature Low Cycle Fatigue Behavior of Materials[R].NASA TMX-52270,7.