Experiment and numerical simulation on characteristic of front variable area bypass injector
-
摘要: 为了研究主、次流的进口总压比及出口背压对前可变面积涵道引射器(FVABI)工作特性的影响与流动掺混机理,采用试验与三维数值模拟方法对不同进口总压比下引射器工作性能及掺混流场随背压变化规律进行了分析。结果表明:标准k -ε模型用于引射器掺混流场的模拟具有较好的准确性;进口总压比越大,引射器总压损失越大;进口总压比不变,随背压增加,引射器总压损失先减小后增加;进口总压比不变,引射器在背压变化过程中存在总压损失最小点;背压减小时,引射器存在临界工况点,且进口总压比越大达到临界工况点的背压越大,可变涵道比的范围变窄;主、次流掺混过程主要集中在沿气流方向上x/l=03~06位置之间,在黏性力作用下动量、质量充分交换,沿流向截面速度径向分布趋于均匀。
-
关键词:
- 前可变面积涵道引射器(FVABI) /
- 掺混机理 /
- 进口总压比 /
- 背压 /
- 总压损失
Abstract: In order to study the effects of inlet total pressure ratio and back pressure on the front variable area bypass injector’s (FVABI) performance and mixing mechanisms, experiment method and three-dimensional numerical simulation approach were applied to analyze the injector’s performance with various inlet total pressure ratios and change regularity of main flow and secondary flow mixing flow fields under different inlet total pressure ratios and back pressures. Results revealed that the standard k -ε model had great accuracy in simulating injector mixing flow field. With the enlargement of inlet total pressure ratio, the total pressure loss of the injector increased. When the inlet total pressure ratio was constant, the total pressure loss increased firstly and then decreased as the back pressure ascended. The injector had an operating point with the minimum total pressure loss as the back pressure changed. When the back pressure reduced, there was a critical operating point for the injector, furthermore the injector’s back pressure was higher at its critical operating point if the inlet total pressure ratio got higher, meaning the adjustable bypass ratio range was narrowed down. The mixing process of the main flow and secondary flow was mainly concentrated in the position of x/l=03-06. The momentum and mass adequately exchanged, and the distribution of velocity was radically uniform along the flow direction. -
[1] 方昌德.变循环发动机[J].燃气涡轮试验与研究,2004,17(3):1-5. FANG Changde.Variable cycle engines[J].Gas turbine experiment and research,2004,17(3):1-5.(in Chinese) [2] 方昌德.变循环发动机及其关键技术[J].国际航空,2004,49(7):49-51. FANG Changde.Variable cycle engine and its key technologies[J].International Aviation,2004,49(7):49-51.(in Chinese) [3] 苟学中,周文祥,黄金泉.变循环发动机部件级建模技术[J].航空动力学报,2013,28(1):104-111. GOU Xuezhong,ZHOU Wenxiang,HUANG Jinquan.Component-level modeling technology for variable cycle engine[J].Journal of Aerospace Power,2013,28(1):104-111.(in Chinese) [4] 刘增文,王占学,黄红超,等.变循环发动机性能数值模拟[J].航空动力学报,2010,25(6):1310-1315. LIU Zengwen,WANG Zhanxue,HUANG Hongchao,et al.Numerical simulation on performance of variable cycle engines[J].Journal of Aerospace Power,2010,25(6):1310-1315.(in Chinese) [5] 陈大光,张津,朱之丽.推重比15一级发动机有关总体性能的关键技术和难点分析[J].航空动力学报,2001,16(1):15-21. CHEN Daguang,ZHANG Jin,ZHU Zhilin.Performance related key technologies and difficulties of engines with thrust to weight ratio up to level of 15[J].Journal of Aerospace Power,2001,16(1):15-21.(in Chinese) [6] JOHNSON J E.Variable cycle engines-the next step in propulsion evolution[R].AIAA 76-0758,1976. [7] BROWN R H.Integration of a variable cycle engine concept in a supersonic cruise aircraft[R].AIAA 78-1049,1978. [8] ALLAN R D.General electric company variable cycle engine technology demonstrator program[R].AIAA 79-1311,1979. [9] SHERWOOD H.Bibliography of supersonic cruise res-earch (SCR) program from 1977 to mid-1980[R].NASA RP-1063,1980. [10] JOHNSON J E.Variable cycle engine developments at General Electric-1955-1995[R].AIAA 97-15033,1997. [11] HINES R W.Variable stream control engine for supers-onic propulsion[J].Journal of Aircraft,1978,15(6):321-325. [12] 周红,王占学,刘增文,等.可变面积涵道引射器对变循环发动机性能影响[J].航空动力学报,2016,31(12):2842-2850. ZHOU Hong,WANG Zhanxue,LIU Zengwen,et al.Impact of variable area bypass injector on variable cycle engine performance[J].Journal Aerospace Power,2016,31(12):2842-2850.(in Chinese) [13] 刘洪波,王荣桥.变循环发动机总体结构和模式转换机构研究[J].航空发动机,2008,34(3):1-5. LIU Hongbo,WANG Rongqiao.Investigation of general structure and mode transiton[J].Aeroengine,2008,34(3):1-5.(in Chinese) [14] 刘宝杰,贾少锋,于贤君.变循环发动机前可调面积涵道引射器的通流计算方法[J].推进技术,2017,38(8):1689-1698. LIU Baojie,JIA Shaofeng,YU Xianjun.Throughflow cal-culation method of variable cycle engine forward varia-ble area bypass injector[J].Journal of Propulsion Technology,2017,38(8):1689-1698.(in Chinese) [15] 张荣,叶志峰,薛义春.变循环发动机模式转换调节计划仿真研究[J].测控技术,2011,34(3):47-50. ZHANG Rong,YE Zhifeng,XUE Yichun.Simulation rese-arch on adjustment plan to mode transition of variable cycle engine[J].Measurement and Control Technology,2011,34(3):47-50.(in Chinese) [16] 王靖宇,张怀宝,黄国平,等.采用射流掺混增强的前可调面积涵道引射器数值模拟[J].国防科技大学学报,2019,41(2):69-74. WANG Jingyu,ZHANG Huaibao,HUANG Guoping,er al.Numerical investigation of front variable area bypass injector with jet mixing enhancement[J].Journal of National University of Defense Technology,2019,41(2):69 -74.(in Chinese) [17] 冷中明,周建华.非轴对称前涵道引射器性能的数值研究[J].推进技术,2015,36(10):1466-1473. LENG Zhongming,ZHOU Jianhua.Numerical investigation for performance of non-axisymmetric for variable area bypass injector[J].Journal of Propulsion Technology,2015,36(10):1466-1473.(in Chinese) [18] 李立国,张靖周.航空用引射混合器[M].北京:国防工业出版社,2007. [19] 单勇,张靖周.波瓣喷管引射-混合器涡结构的数值研究[J].空气动力学报,2005,23(3):355-359. SHAN Yong,ZHANG Jingzhou.Numerical investigation of vortical structures in the lobed mixer-ejector[J].Acta Aerodynamica Sinica,2005,23(3):355-359.(in Chinese)
点击查看大图
计量
- 文章访问数: 512
- HTML浏览量: 3
- PDF量: 586
- 被引次数: 0