航天推进技术研究院主办
[1]贺 宏,丁佳伟,冷海峰,等.发动机用扩压器性能及扩压器后射流数值分析[J].火箭推进,2021,47(05):71-77.
HE Hong,DING Jiawei,LENG Haifeng,et al.Numerical analysis of the performance of the diffuser for rocket engine and the gas jet after the diffuser[J].Journal of Rocket Propulsion,2021,47(05):71-77.
点击复制
HE Hong,DING Jiawei,LENG Haifeng,et al.Numerical analysis of the performance of the diffuser for rocket engine and the gas jet after the diffuser[J].Journal of Rocket Propulsion,2021,47(05):71-77.
发动机用扩压器性能及扩压器后射流数值分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
47
期数:
2021年05期
页码:
71-77
栏目:
研究与设计
出版日期:
2021-10-28
- Title:
- Numerical analysis of the performance of the diffuser for rocket engine and the gas jet after the diffuser
- 文章编号:
- 1672-9374(2021)05-0071-07
- 关键词:
- 扩压器性能 燃气射流 数值研究 环境设计
- 分类号:
- V414.1
- 文献标志码:
- A
- 摘要:
- 扩压器是火箭发动机进行高空模拟试验的重要地面设备,针对某空气泄入式圆筒型扩压器设计参数进行了数值研究,同时对该扩压器后的燃气射流进行了分析。计算结果表明,扩压器直径是影响扩压器性能的一个重要参数,在满足喷管出口满流的前提下,当扩压器直径增大时,带来的是总压损失逐渐增大,扩压器内激波串的强度逐渐增强 长径比并不是一个影响扩压器流场和起动情况的独立参数,该参数的选取与发动机工况状态和结构状态相关 泄入间隙的选择可根据发动机的工况进行设计。对扩压器后的燃气射流计算表明,与不带扩压器的喷管燃气射流相比,由于燃气在扩压器内总压损失较自由射流小,扩压器后的燃气射流具有影响区域范围大的特点,该计算结果可为发动机地面试验不同条件下燃气射流提供一定的预示,对试验过程中燃气射流引起的环境设计提供借鉴。
- Abstract:
- The diffuser is an important ground equipment for high altitude simulation test of rocket engines. The design parameters of an air-bleed cylinder diffuser were studied numerically,and the gas jet after the diffuser was analyzed. The results show that the diffuser diameter is an important parameter affecting the diffuser performance. When the diffuser diameter increases,the total pressure loss increases and the intensity of shock wave in the diffuser increases. The length-diameter ratio is not an independent parameter affecting the diffuser flow field and start-up. The selection of the parameters is related to the engine working condition and structure condition,and the selection of the leakage gap can be designed according to the engine working condition. The calculation of the gas jet after the diffuser shows that,compared with the nozzle gas jet without the diffuser,the gas jet after the diffuser has the characteristics of large area because the total pressure loss of the gas in the diffuser is smaller than that of the free jet. It provides a reference for the environmental design caused by gas jet during the test.
参考文献/References:
[1] 叶正寅,吕广亮.火箭发动机喷管非定常侧向力和流固耦合研究进展[J].航空工程进展,2015,6(1):1-12. [2] 于洋.RBCC单边膨胀喷管过膨胀流动分离现象及机理研究[D].南京:南京航空航天大学,2017. [3] 张民庆,张忠利,周立新,等.超声速自引射装置的工作过程研究[J].航空动力学报,2012,27(1):218-224. [4] 杨建文,付秀文,刘占一,等.等截面引射器启动性能数值研究[J].应用力学学报,2014,31(5):697-702. [5] 吴薇梵,王占林,孔凡超,等.环形引射器两相流动数值模拟[J].火箭推进,2020,46(4):31-37.WU W F,WANG Z L,KONG F C,et al.Numerical simulation with two-phase flow in annular ejector[J].Journal of Rocket Propulsion,2020,46(4):31-37. [6] 秦永涛,唐斌运,沈继彬,等.液氧/煤油发动机试验扩压器热力耦合特性分析[J].火箭推进,2016,42(1):71-76.QIN Y T,TANG B Y,SHEN J B,et al.Analysis on thermal mechanical coupling characteristics of diffuser in test of liquid oxygen/kerosene rocket engine[J].Journal of Rocket Propulsion,2016,42(1):71-76. [7] 杨建文,刘计武,石晓波,等.启动过程对大膨胀比喷管外压失稳的影响研究[J].推进技术,2016,37(6):1182-1188. [8] 孙顺利,李纲.高空模拟引射器启动特性的实验和数值计算研究[J].弹箭与制导学报,2017,37(4):63-67. [9] 蔡红华,聂万胜,苏凌宇,等.液氧煤油发动机尾焰冲击导流槽三维数值模拟[J].工程热物理学报,2017,38(10):2202-2207. [10] 乔野,聂万胜,丰松江,等.液氢/液氧火箭发动机尾焰流场特性仿真研究[J].火箭推进,2015,41(5):43-48.QIAO Y,NIE W S,FENG S J,et al.Simulation research on fluid field characteristics of LH2/LOX rocket engine plume[J].Journal of Rocket Propulsion,2015,41(5):43-48. [11] 张磊,王浩,阮文俊,等.超声速燃气射流流场特性的三维数值模拟[J].弹道学报,2015,27(2):80-84. [12] 徐悦,周旭,张志成,等.火箭发动机燃气射流喷水降噪研究[J].航空动力学报,2010,25(4):816-820. [13] 杜伟,田晓丽,白敦卓,等.外界环境和二次燃烧对喷管射流影响研究[J].现代防御技术,2016,44(6):31-36. [14] 蔡红华,聂万胜,丰松江.复燃对液氧煤油发动机尾焰冲击特性影响研究[J].推进技术,2016,37(10):1922-1927. [15] 蔡红华,聂万胜,侯志勇.液体火箭发动机尾焰对发射平台冲击效应[J].航空动力学报,2016,31(8):1995-2001. [16] 李爱琴,李军伟,王宁飞.火箭发动机自由射流噪声模拟过程[J].计算机仿真,2014,31(12):64-68. [17] 陈明.几种湍流模型对超燃发动机冷态流场的数值模拟[J].机电技术,2013,36(2):87-89. [18] 杨肖峰.火星探测器气动力热和传热特性研究[D].绵阳:中国空气动力研究与发展中心,2013. [19] 圆柱形外喷雾冷却扩压器装置设计规范[S].航天工业总公司零六七基地地基标准,1996. [20] 赵承庆,姜毅.气体射流动力学[M].北京:北京理工大学出版社,1998.
备注/Memo
基金项目:国防基础科研项目(JCKY202003XXXX)
作者简介:贺宏(1986—),男,硕士,高级工程师,研究领域为液体火箭发动机试验技术。
更新日期/Last Update:
1900-01-01