Adaptability of cooling structure schemes of liquid propellant rocket engine thrust chamber under different pressures
-
摘要:
为了精准评估不同冷却方案对高压液氧烃火箭发动机推力室传热特性的影响,建立了一套再生通道-液膜屏蔽-隔热镀层-辐射换热的整机模型,采用Ievlev半经验模型计算燃气侧壁面的对流换热过程,引入Shruvik安全裕度评估准则,计算推力室径向的分区温度和热流密度。基于某型大推力液氧煤油火箭发动机,研究了不同冷却结构组合的换热能力上限,分析了不同推力室压力对冷却设计方案的影响。结果表明:推力室压力在12 MPa及以下时,可主要依靠再生冷却技术满足冷却需求;在16 MPa及以下时需要配合内冷却环带满足冷却需求;在18 MPa及以下时需进一步设置隔热镀层提高热防护能力;室压在20 MPa甚至更高时,必须采用其他强化换热措施。
Abstract:In order to accurately evaluate the effect of different cooling schemes on the heat transfer characteristics of thrust chamber of high-pressure liquid oxygen and hydrocarbon rocket engine, a complete model combining regenerative channel, liquid film shield, thermal barrier coating and radiation heat transfer was established. The Ievlev semi-empirical model was adopted for calculation of convection on gas wall. The Shruvik safety margin evaluation criterion was used in analysis. The radial direction multi-layer temperature and heat flux of the thrust chamber were calculated. Based on a large thrust liquid oxygen and kerosene rocket engine, the upper limit of heat transfer capacity of different cooling schemes was studied, and the influence of different thrust chamber pressures on cooling design was analyzed. Results showed that, thrust chamber can mainly rely on regenerative cooling technology to meet the cooling requirements at 12 MPa or below; film cooling slots should be further used at 16 MPa or below; thermal barrier coating should be further installed at 18 MPa or below; several intensive cooling measures must be adopted at 20 MPa or higher.
-
表 1 冷却通道温度上限参考
Table 1. Limit temperature reference of cooling channel
参数 理论上限 安全裕度 最终上限 Tg/K <1100 100 <1000 Tw/K <900 100 <800 Tl/K <650 60 <590 Tc/K <470 20 <450 表 2 液体火箭发动机模型参数
Table 2. Model parameters of the LRE
参数 数值及说明 喷注器 同轴离心式 燃烧室 圆柱形 圆柱段长度/mm 300 喷管喉径/mm 220 喉部收缩比 2.9 喷管扩张比 36 冷却方式 再生冷却+液膜环带 材料 高导热铜合金(推力室内壁) 高强度不锈钢(推力室外壁) 镍铬镀层(隔热镀层) 表 3 冷却剂温升试验校验数据
Table 3. Coolant temperature rise test verification data
试验序号 温升/K 误差/% 试验值 计算值 1 130.8 124.8 −4.59 2 126.0 124.7 −1.03 3 119.2 121.9 2.27 4 118.7 120.2 1.26 5 124.4 119.4 −4.02 表 4 不同冷却方案的结构设计
Table 4. Structure design of different cooling schemes
序号 压强/MPa 冷却技术 再生
冷却小流量
环带大流量
环带隔热
镀层A-1 12 √ √ A-2 16 √ √ A-3 18 √ √ A-4 20 √ √ B-1 12 √ √ B-2 16 √ √ B-3 18 √ √ B-4 20 √ √ C-1 12 √ √ √ C-2 16 √ √ √ C-3 18 √ √ √ C-4 20 √ √ √ 表 5 16 MPa案例工况参数
Table 5. Operating parameters of the case using 16 MPa
工况参数 数值 推力室压力/MPa 16.00 冷却通道压力/MPa 21.83 氧化剂总流量/(kg/s) 259.7 燃料总流量/(kg/s) 90.7 中心区混合比 2.9 边区混合比 2.0 -
[1] 中国航天工业总公司. 世界导弹与航天发动机大全[M]. 北京: 军事科学出版社, 1999. [2] 黄望梅, 贺晨, 张振启, 等. SpaceX星舰运载系统发展分析与启示[R]. 兰州: 第2届未来空间技术高峰论坛, 2021. [3] 侯瑞峰, 陈建华, 曹晨. 高室压液氧烃发动机冷却结构适应性分析[R]. 昆明: 中国航天第三专业信息网第40届技术交流会, 2019. [4] 李勋锋,仲峰泉,范学军,等. 超临界压力下航空煤油水平管内对流换热特性数值研究[J]. 航空动力学报,2010,25(8): 1690-1697. LI Xunfeng,ZHONG Fengquan,FAN Xuejun,et al. Numerical study of convective heat transfer characteristics of kerosene flowing in a horizontal pipe at supercritical pressure[J]. Journal of Aerospace Power,2010,25(8): 1690-1697. (in Chinese doi: 10.13224/j.cnki.jasp.2010.08.028 [5] 王慧洁,许坤梅. 液体火箭发动机燃烧室壁液膜冷却的数值模拟[J]. 航空动力学报,2018,33(11): 2660-2668. WANG Huijie,XU Kunmei. Numerical simulation of liquid film cooling for combustion chamber wall of liquid rocket engine[J]. Journal of Aerospace Power,2018,33(11): 2660-2668. (in Chinese doi: 10.13224/j.cnki.jasp.2018.11.012 [6] PERAKIS N,PREIS L,HAIDN O J,et al. Wall heat flux evaluation in regeneratively cooled rocket thrust chambers[J]. Journal of Thermophysicsand Heat Transfer,2020,35(10): 1-15. [7] PIZZARELLI M. An algebraic model for structural and life analysis of regeneratively-cooled thrust chambers[J]. Journal of Propulsion and Power,2020,36(2): 191-201. doi: 10.2514/1.B37669 [8] STROKACH E A,BOROVIK I N,BAZAROV V G,et al. Numerical study of operational processes in a GOx-kerosene rocket engine with liquid film cooling[J]. Propulsion and Power Research,2020,9(2): 132-141. doi: 10.1016/j.jppr.2020.04.004 [9] 王堃,王国强. 双组元推力室热防护涂层工艺技术研究[J]. 火箭推进,2020,9(2): 132-141. WANG Kun,WANG Guoqiang. Research on thermal protection coating technique of bipropellant thrust chamber[J]. Journal of Rocket Propulsion,2020,9(2): 132-141. (in Chinese [10] HAN P G, NAMKOUNG H J, KIM K H. A study on the cooling mechanism in liquid rocket engine[R]. AIAA-2004-3672, 2004. [11] HAN P G, NAMKOUNG H J, KIM K H, et al. A Study on heat transfer characteristics of small liquid rocket engine with calorimeter[R]. AIAA-2006-5195, 2006. [12] 张其阳,王兵,张会强,等. 液膜内冷与辐射外冷发动机室压上限的研究[J]. 推进技术,2013,34(6): 781-785. ZHANG Qiyang,WANG Bing,ZHANG Huiqiang,et al. A study on chamber pressure upper limit of liquid rocket engine utilizing film and radiative cooling[J]. Journal of Propulsion and Power,2013,34(6): 781-785. (in Chinese doi: 10.13675/j.cnki.tjjs.2013.06.016 [13] 谭建国,王振国. 三组元液体火箭发动机系统方案设计与比较[J]. 推进技术,2003,24(5): 406-409. TAN Jianguo,WANG Zhenguo. Design and comparison of tripropellantliquid rocket engine system scheme[J]. Journal of Propulsion and Power,2003,24(5): 406-409. (in Chinese doi: 10.3321/j.issn:1001-4055.2003.05.005 [14] 孙冰, 张建伟. 火箭发动机热防护技术[M]. 北京: 北京航空航天大学出版社, 2016. [15] 杨立军, 富庆飞. 液体火箭发动机推力室设计[M]. 北京: 北京航空航天大学出版社, 2013. [16] 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. [17] 张其阳. 液体火箭发动机推力室结构与冷却设计[D]. 北京: 清华大学, 2012.ZHANG Qiyang. Structure and cooling design of liquid rocket engine thrust chamber[D]. Beijing: Tsinghua University, 2012. (in Chinese) [18] 杨世铭, 陶文铨. 传热学[M]. 北京: 高等教育出版社, 2006. [19] 杨宝庆,陈建华,周立新. 推力室多条内冷却环带近壁燃气混合比计算新模型[J]. 火箭推进,2002,28(4): 20-26. YANG Baoqing,CHEN Jianhua,ZHOU Lixin. A new model for calculation of normal wall gas mixing ratio of multiple internal cooling slots zone[J]. Journal of Rocket Propulsion,2002,28(4): 20-26. (in Chinese [20] 什维留克M H. 液体火箭发动机的设计理论基础[M]. 包雨相, 赵国光, 彭永龄, 译. 上海: 上海科学技术出版社, 1963. [21] GREUEL D, SUSLOV D, HAIDN O J, et al. Thermal barrier coatings for cryogenic rocket[R]. AIAA-2002-4145, 2002. [22] 陈建华,杨宝庆,周立新,等. 人为粗糙度强化换热机理分析及效果评估[J]. 火箭推进,2004,30(4): 1-5. CHEN Jianhua,YANG Baoqing,ZHOU Lixin,et al. The mechanism and effect of artificial roughness on heat transfer enhancement[J]. Journal of Rocket Propulsion,2004,30(4): 1-5. (in Chinese doi: 10.3969/j.issn.1672-9374.2004.04.001 [23] CARLILE J, QUENTMEYER R. An experimental investigation of high-aspect ratio cooling passages[R]. AIAA-1992-3154, 1992.