Model for three-dimensional distribution of liquid fuel in supersonic crossflows
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摘要: 针对超声速气流中液体横向射流的空间振荡分布特性开展试验研究，建立射流/喷雾在纵向和三维空间内的振荡分布预测模型。试验在Ma2.1下吹式风洞中进行，采用脉冲激光背景成像方法和基于PIV原理的倾斜成像方法分别捕捉纵向和不同横截面上的喷雾瞬态分布结构，涉及的研究参数及其变化范围包括：超声速来流总压（642~1010kPa）、液体喷孔直径（0.48~2.07mm）、距离喷孔的流向距离（10~125mm）以及液气动量比（0.11~10）。通过研究，提出并定义一种用于定量描述射流/喷雾空间振荡分布的无量纲参数——喷雾分数（γ），基于喷雾分数开展了纵向喷雾振荡分布研究，建立了纵向边界带模型，并开展了模型准确性验证。研究并发现了横截面上喷雾振荡分布呈"Ω"型，提出spray body和spray foot的分区概念，构造egg-shape曲线对spray body区域的喷雾分数等值线进行拟合，建立了egg-shape曲线方程中6个关键系数的系数模型，进而建立了超声速气流中液体横向射流空间振荡分布预测模型。Abstract: The spatial oscillation distribution characteristics of liquid jet in a supersonic crossflow were studied experimentally. Two models were built for predicting the oscillation distribution in the longitudinal and three-dimensional space, respectively. The experiments were carried out in a blow-type wind tunnel with Mach number of 2.1, and various conditions were studied, including stagnation pressure of the supersonic airflow (642~1010kPa), nozzle diameters (0.48~2.07mm), distance down from nozzle (10~125mm), practical pressure ranges (0.5~4.5MPa), and jet-gas momentum flux ratio ranges (0.11~10). Pulse laser background imaging method (PLBI) was used to shoot the transient spray distribution structures from the side and PIV method was used to capture the structures in cross-sections. A key parameter (Spray Proportion, γ) was defined to quantify the spatial oscillation distribution of the spray. A longitudinal spray oscillation distribution study was carried out, a spray boundary band model was established, and the model accuracy was verified. In addition, a piecewise function of the egg-shape curve and parabola was adopted to fit the contour line to establish the model for the spatial distribution of the spray in the cross-section. Based on various cross-section distributions with multi-parameters, a mathematical model is proposed to describe the liquid spray spatial distribution.
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Key words:
- scramjet /
- liquid jet /
- atomization /
- oscillation distribution
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图 2 风洞试验段速度分布云图(x=0为喷射位置)
Figure 2. The airflow velocity distribution in test section (PIV result), 'x=0' is the injection position
图 5 不同时刻横截面液雾瞬态分布(零时刻为开阀喷注起始时间)
Figure 5. Cross-section distributions of the spray at four random moments in case 54
图 7 多参数协同作用对边界带的影响
Figure 7. The spray boundary zones under various operating conditions
图 9 全部工况下γ=0.5对应边界曲线的拟合
Figure 9. Fitting result of the experimental results for γ=0.5
图 10 边界带模型预测效果(验证试验工况参数：喷射介质为水; 喷孔直径d=1.0mm; 喷注压降pl=1.49MPa; Ma=2.1;液气动量通量比q=3.8)
Figure 10. Evaluation of the accuracy of the model
图 12 d和q不变的条件下，液雾横截面分布随x的变化
Figure 12. Impact on the spray's cross-section distribution when x changes (d and q keep constant)
图 13 d和x不变的条件下，液雾横截面分布随q的变化
Figure 13. Impact on the spray's cross-section distribution when q changes (d and x kept constant)
表 1 工况参数表(表中Ma为气流马赫数，T0为气流总温，p0为气流总压，d为喷嘴流道直径，l为喷嘴流道长度，Δp为液体喷注压降，Vl为射流出口平均速度，q为液气动量比)
Table 1. The list of key parameters (Ma is mach number, T0 is stagnation temperature, p0 is stagnation pressure, d is nozzle diameter, l is nozzle length, Δp is injection pressure, Vl is velocity of liquid jet, q is momentum flux ratio of liquid to gas)
No. Supersonic crossflow (Ma=2.1; T0=300K) Kerosene jet (density: 800kg/m3; l=1.5mm) p0/kPa d/mm Δp /MPa Vl /(m·s-1) q 1~8 920 1.52 0.48~3.93 23~69 0.68~6.16 9/10 714 1.52 0.43/1.24 22/38 0.84/2.46 11/12 792 1.52 0.48/1.35 23/40 0.82/2.41 13~18 923 1.25 0.58~4.10 22~61 0.62~4.85 19 1010 1.25 1.92 41 2.04 20 820 1.25 1.87 41 2.47 21 719 1.25 2.26 45 3.44 22 645 1.25 2.00 43 3.40 23~29 915 1.00 0.36~4.61 18~72 0.42~6.84 30~32 797 1.00 2.81~4.39 57~71 4.97~7.49 33~36 795 0.48 0.63~4.55 15~23 0.11~0.78 37 642 0.48 4.33 22 0.92 38 742 0.48 4.37 23 0.80 39 947 0.48 4.37 23 0.63 40 1.00 3.80 
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表 2 工况参数表(表中Ma为气流马赫数，T0为气流总温，p0为气流总压，d为射流喷孔直径，q为液气动量比)
Table 2. The list of key parameters (Ma is mach number, T0 is stagnation temperature, p0 is stagnation pressure, d is nozzle diameter, q is momentum flux ratio of liquid to gas)
No. d/mm x/d q Gas crossflow 41~44 0.68 100 1.6/3.4/6.1/10 Ma=2.1 45~46 0.99 10 3.7/5.5 T0=300K 47~48 0.99 20 3.9/5.7 p0=891kPa 49 0.99 30 3.9 50~51 0.99 50 3.9/5.6 52 0.99 70 3.9 Water Jet 53~56 0.99 100 3.9/5.6/7.4/9 ρ=1000kg/m3 57~60 1.25 100 1.1/2.4/3.7/4.9 Tw=300K 61~64 1.51 66 1.4/2.7/4.1/5.5 65 2.07 10 2.3 66 2.07 30 1.1 67 2.07 45 2.3
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