火箭推进

研究了一种二维超声速进气道扩张段型面的中心线变化规律、扩张比及中心线偏距对设计状态下进气道的气动性能及流场的影响。结果表明:采用前缓后急中心线变化规律的进气道出口总压恢复系数最高,而采用前急后缓中心线变化规律的进气道总压恢复系数最低; 随着扩张比从1.40增大到1.80,进气道总压恢复系数和抗反压能力均下降,出口马赫数上升, 扩张比与长度对进气道出口参数的影响存在较强的耦合关系; 随着偏距比的增加,进气道总压恢复系数起初有一定的升高,但偏距比增大到0.80之后,总压恢复系数降低,出口马赫数增大,总体上偏距比变化对进气道抗反压能力影响不大。

The influences of the law of centerline variation, expansion ratio and centerline offset of two-dimensional supersonic inlet diffuser on aerodynamic performance and flow characteristics under inlet design condition are studied. The numerical results indicate that the inlet with diffuser rapid turning at its exit has maximum total pressure recovery coefficient and inlet with diffuser rapid turning at the entrance has minimum total pressure recovery coefficient; as the expansion ratio increases from 1.40 to 1.80, inlet total pressure recovery coefficient and backpressure-resistance ability decrease, and the exit Mach number increase; the effect of expansion ratio and length on inlet exit parameter has a strong coupling relationship. As offset ratio increases, the inlet total pressure recovery coefficient increases at the beginning, but as the offset ratio increases to more than 0.80, the inlet total pressure recovery coefficient declines and the exit Mach number increases. General speaking, the variation of offset ratio has little effect on backpressure-resistance ability of the inlet.

引言
1 物理模型和计算方法
2 扩张段型面参数对进气道性能的影响
3 结论

图1 进气道模型
Fig.1 Inlet model

图2 三种扩张段下进气道出口总压恢复系数随反压的变化曲线<br/>Fig.2 Variation of total pressure recovery coefficient at inlet exits of three kinds of diffusers with backpressure

图2 三种扩张段下进气道出口总压恢复系数随反压的变化曲线
Fig.2 Variation of total pressure recovery coefficient at inlet exits of three kinds of diffusers with backpressure

图3 反压为16p0下三种扩张段内压力云图<br/>Fig.3 Pressure contours of three kinds of diffusers with backpressure at 16p0

图3 反压为16p0下三种扩张段内压力云图
Fig.3 Pressure contours of three kinds of diffusers with backpressure at 16p0

图4 临界状态下三种扩张段内压力云图<br/>Fig.4 Internal pressure contours of three kinds of diffusers at critical condition

图4 临界状态下三种扩张段内压力云图
Fig.4 Internal pressure contours of three kinds of diffusers at critical condition

图5 L1型面背景波系图<br/>Fig.5 Background waves in diffuser of L1shape

图5 L1型面背景波系图
Fig.5 Background waves in diffuser of L1shape

图6 L1扩张段壁面激波串前缘点位置随压力变化曲线<br/>Fig.6 Variation of leading point position of shock wave train in diffuser of L1 shape with pressure

图6 L1扩张段壁面激波串前缘点位置随压力变化曲线
Fig.6 Variation of leading point position of shock wave train in diffuser of L1 shape with pressure

图7 临界状态下进气道出口总压恢复系数随扩张比变化曲线<br/>Fig.7 Variation of total pressure recovery coefficient at inlet exit at critical condition with diffusing ratio

图7 临界状态下进气道出口总压恢复系数随扩张比变化曲线
Fig.7 Variation of total pressure recovery coefficient at inlet exit at critical condition with diffusing ratio

图8 临界状态下不同扩张比扩张段的压力云图<br/>Fig.8 Pressure contours in diffuser with different diffusing ratios at critical condition

图8 临界状态下不同扩张比扩张段的压力云图
Fig.8 Pressure contours in diffuser with different diffusing ratios at critical condition

图9 临界状态下进气道出口性能参数随偏距变化曲线<br/>Fig.9 Variation of performance parameters of inlet exit at critical condition with centerline offset

图9 临界状态下进气道出口性能参数随偏距变化曲线
Fig.9 Variation of performance parameters of inlet exit at critical condition with centerline offset

图10 临界状态下不同偏距扩张段的压力云图<br/>Fig.10 Pressure contours in diffuser with differentcenterline offsets at critical condition

图10 临界状态下不同偏距扩张段的压力云图
Fig.10 Pressure contours in diffuser with differentcenterline offsets at critical condition

[1] SAJBEN M, BOGAR T J, KROUTIL J C. Expermental study of flows in a two-dimensional inlet model [J]. Journal of propulsion and power, 1985, 1(2): 109-117.
[2] SAJBEN M, BOGAR T J, KROUTIL J C. Experimental investigation of terminal shock sensors for mixed-compression inlets [J]. Journal of propulsion and power, 1992, 8(1): 168-174.
[3] BOGAR T J, SAJBEN M, KROUTIL J C. Characteristics frequencies of transonic diffuser flow oscillations [J]. AIAA journal, 1983, 21(9): 1232-1240.
[4] IKUI T, MATSUO K, MOCHIZUKI H, et al. Pseudo-shock waves in a divergent channel [J]. Bull JSME,1980, 23(175): 20-25.
[5] IKUI T, MATSUO K, SASAGUCHI K. Modified diffusion model of pseudo-shock waves considering upstream boundary layer [J]. Bull JSME, 1981, 24(197): 1920-1927.
[6] HSIEH T, WARDLAW A B, COAKLEY T. Ramjet diffuser flowfield response to large-amplitude combustor pressure oscillations [J]. Journal of propulsion and power, 1987, 3(5): 472-477.
[7]HSIEH T, BOGAR T J, COAKLEY T. Numerical simulation and comparison with experiment for self-excited oscillations in a diffuser flow [J]. AIAA journal, 1987, 25(7): 936-943.
[8] KAWATSU K, KOIKE S, KUMASAKA T, et al. Pseudo-shock wave produced by backpressure in straight and diverging rectangular ducts [C]//Proceedings of AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. [S.l.]: AIAA, 2005: 2005-3285.
[9] WEISS A, GRZONA A, OLIVIER H. Behavior of shock trains in a diverging duct [J]. Exp fluids, 2010, 49: 355-365.
[10] WEISS A, OLIVIER H. Behavior of a shock train under the influence of boundary-layer suction by a normal slot [J]. Exp fluids, 2012, 52: 273-287.
[11] HYOUNG J L, BOK J L. Flow characteristics of small-sized supersonic inlets [J]. Journal of propulsion and power, 2011, 27(2): 306-318.
[12] 谭慧俊,郭荣伟. 二维弯曲等截面管道中的激波串特性研究[J].航空动力学报,2006,27(6):1039-1045.
[13] TAN Huijun, SUN Shu. Preliminary study of shock train in a curved variable-section diffuser [J]. Journal of propulsion and power, 2008, 24(2): 245-252.
[14] 安彬,范晓樯,李腾骥,等. 等截面S弯隔离段流场特性研究[R].第十七届中国空气动力学物理气体动力学学术交流会, 2015.
[15] GUO Shanguang, WANG Zhenguo, ZHAO Yuxin. Contour design of super / hypersonic dual-Inflection nozzle [J]. Journal of aerospace power, 2012, 27( 12): 2742 -2748.
[16] 郭善广,王振国,赵玉新. 超声速转弯流道内的迟滞现象[J]. 国防科技大学学报, 2014, 36(4): 10-14.
[17] LEE C, BOEDICKER C. Subsonic diffuser design and performance for advanced fighter aircraft: AIAA 85-3073 [R]. USA: AIAA, 1985.
[18] REINARTZ B U, HERRMAN C D, BALLMANN J. Aerodynamic performance analysis of a hypersonic inlet isolator using computation and experiment [J]. Journal of propulsion and power, 2003, 19(5): 868-875.

备注

引言

1 物理模型和计算方法

2 扩张段型面参数对进气道性能的影响

3 结论

期刊信息