Lean ignition performance of trapped vortex cavity afterburner with different cavities
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摘要:
为了研究凹腔结构参数对驻涡加力燃烧室贫油点火性能影响规律，设计了3种凹腔进气缝宽度、两种凹腔外廓结构的试验件。采用试验研究方法，对不同试验件方案、不同气流参数下驻涡加力燃烧室点火性能进行研究。试验马赫数为0.17～0.3、压比为0.97～1.08。获得了驻涡加力燃烧室点火马赫数边界、点火油气比变化规律和预测方法。结果表明：随着马赫数和压比增加，贫油点火油气比增加；较大外廓结构、较小进气缝宽度的凹腔稳定器点火性能更加优异；计算模型可有效预测贫油点火油气比，预测精度在20%以内。
Abstract:Three different kinds of mixed air gaps and two different kinds of cavity structures were designed to study the lean ignition performance of trapped vortex cavity afterburner. The experimental researches with different cavities and flow parameters were carried out. The investigation was performed with the mainstream Mach number ranging from 0.17 to 0.3, the pressure ratio of secondary flow to mainstream flow ranging from 0.97 to 1.08. The ignition Mach number, fuel air ratio and predictive model of the trapped vortex cavity afterburner were obtained. The results showed that the fuel air ratio increased with the increasing mainstream Mach number and the pressure ratio of secondary flow to mainstream flow. The bigger cavity with smaller mixed air gap was better for ignition. A predictive model was developed for the fuel air ratio. The error between the predicted value and the experimental value was not greater than 20%.
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图 7 两种凹腔结构下贫油点火性能随马赫数变化
Figure 7. Lean ignition performance of two trapped vortex cavity schemes versus Mach number
图 8 两种凹腔结构下贫油点火性能随压比变化
Figure 8. Lean ignition performance of two trapped vortex cavity schemes versus pressure ratio
图 9 3种凹腔结构下贫油点火性能随马赫数变化
Figure 9. Lean ignition performance of three trapped vortex cavity schemes versus Mach number
图 10 3种凹腔结构下贫油点火性能随压比变化
Figure 10. Lean ignition performance of three trapped vortex cavity schemes versus pressure ratio
图 11 凹腔点火过程壁温变化
Figure 11. Wall temperature changes during ignition of trapped vortex cavity
图 12 不同方案F预测值与试验值对比
Figure 12. Comparison of measured and predicted values of F for different schemes
表 1 4种不同方案的凹腔结构参数
Table 1. Parameters of four different trapped vortex cavity schemes
mm 方案 L1 L2 L H1 H2 H3 A 45 42 50 2.5 2.5 2.5 B 45 42 50 1.6 1.6 1.6 C 45 42 50 3 3 3 D 40.5 37.8 45 2.5 2.5 2.5 
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表 2 试验工况
Table 2. Experimental conditions
参数 数值 工况1 工况2 工况3 工况4 工况5 工况6 工况7 工况8 工况9 外涵进气温度T23/K 500 外涵进口压力p23/kPa 182 182 182 182 175 187 194 182 107 内涵进气温度T6/K 750 内涵进口压力p6/kPa 180 180 180 180 180 180 180 180 110 外涵/内涵压比rp 1.01 1.01 1.01 1.01 0.97 1.04 1.08 1.01 1.01 内涵马赫数 0.17 0.2 0.23 0.26 0.23 0.23 0.23 0.3 0.23
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表 3 4种不同方案凹腔进气流量
Table 3. Cavity air flow of four different trapped vortex cavity schemes
% 方案 凹腔进气流量占总空气流量的比例 工况1 工况2 工况3 工况4 工况5 工况6 工况7 工况8 工况9 A 2.87 2.86 2.92 2.97 2.69 3.16 3.41 2.99 2.95 B 1.99 1.99 2.05 2.1 1.67 2.27 2.49 2.14 2.1 C 3.14 3.13 3.18 3.25 2.92 3.34 3.62 3.27 3.32 D 2.77 2.79 2.81 2.87 2.57 3.05 3.38 2.89 2.86
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表 4 点火试验结果
Table 4. Experimental results for ignition
方案 升温时间/s ΔT=5 K ΔT=100 K A 2.0 4.7 B 1.8 4.1 C 5.8 8.2 D 13.5 16.3
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表 5 方案B点火油气比预测与试验对比
Table 5. Comparison of measured and predicted values of fuel air ratio for scheme B
工况 F预测值 F试验值 误差/% 1 0.00171 0.00197 13.2 2 0.00188 0.00196 4.1 3 0.00216 0.00219 1.4 4 0.00253 0.00222 −13.9 5 0.00184 0.00179 −2.7 6 0.00240 0.00245 2.0 7 0.00258 0.00250 −3.2 8 0.00288 0.00270 −6.7 9 0.00315 0.00302 −4.3
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