Scheme and Performance Analysis of a Hybrid Power System for Two Stroke Aviation Heavy Fuel Piston Engine
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摘要:
面向高功率密度和低耗油率，提出了一种航空活塞-涡轮复合循环动力系统构型，活塞子系统采用气缸水平对置的二冲程航空重油活塞发动机，涡轮机子系统由燃烧器和涡轮增压器组成。基于GT-POWER平台，采用缸压对比研究的方法验证了仿真模型的准确性。基于仿真模型研究了增压器效率、涡轮效率、补燃油量及海拔高度对复合循环动力系统性能的影响，并依据油耗与输出扭矩进行系统性能评估。研究结果表明，与单一航空活塞发动机相比，混合动力系统在极限状态下能将输出扭矩提升约30%；压气机效率提升10%产生的扭矩增益大于涡轮效率提升10%产生的扭矩增益；涡轮前补燃燃油流量在0.2 g/s时，能够将排温提升约150 K，所有工况点输出扭矩提升20%以上。因此，涡轮前补燃是提升航空活塞-涡轮混合动力系统性能的有效手段。
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关键词:
- 二冲程航空活塞 /
- 混合动力系统 /
- GT-POWER模拟 /
- 涡轮子系统效率 /
- 补燃
Abstract:In response to high power density and low fuel consumption, an aviation piston-turbine hybrid system configuration was proposed, wherein the piston subsystem adopted a two-stroke aviation heavy oil piston engine with horizontally opposed cylinders, and the turbine subsystem consisted of a burner and a turbocharger. Based on the GT-POWER platform, the accuracy of the simulation model was verified using a comparative study of cylinder pressure. The effects of turbocharger efficiency, turbine efficiency, reheat fuel flow, and altitude on the performance of hybrid system were studied, and the system performance was evaluated based on brake specific fuel consumption and output torque. The research results showed that the hybrid system can increase the output torque by about 30% compared with the aviation piston engine at the limit state. The torque gain generated by a 10% increase in compressor efficiency was greater than the torque gain generated by a 10% increase in turbine efficiency. When the fuel flow rate in front of the turbine was 0.2 g·s−1, the exhaust temperature can be increased by about 150 K, and the output torque at all operating points can be increased by more than 20%. Therefore, reheating in front of a turbine is an effective means to improve the performance of an aviation piston-turbine hybrid system.
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Key words:
- two-stroke aviation piston /
- hybrid system /
- GT-POWER simulation /
- turbine subsystem efficiency /
- reheat
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图 6 活塞-涡轮混合动力系统的一维仿真模型
Figure 6. One-dimensional simulation model of piston turbine hybrid system
图 7 扫气时面值随曲轴转角的变化
Figure 7. Change of face value with crankshaft angle during scavenging
图 8 1800 r/min和2400 r/min缸压曲线对比图
Figure 8. Comparison Diagram of Cylinder Pressure Curves at 1800 r/min and 2400 r/min
图 9 1800 r/min时BSFC随复合转矩变化图
Figure 9. Variation of BSFC with composite torque at 1800 r/min
图 10 2400 r/min时燃油消耗随复合扭矩的变化
Figure 10. Change of fuel consumption with combined torque at 2400 r/min
图 11 1800 r/min时不同压气机和涡轮等熵效率对BSFC的影响
Figure 11. Effects of different isentropic efficiencies of compressors and turbines on BSFC at 1800 r/min
图 12 2400 r/min不同压气机和涡轮效率对BSFC和曲轴转矩的影响
Figure 12. Effects of Different Compressor and Turbine Efficiency at 2400 r/min on BSFC and Crankshaft Torque
图 13 不同程度的补燃BSFC随输出扭矩的变化图
Figure 13. Variation diagram of staged combustion BSFC with different degrees of output torque
图 14 1800 r/min时补燃对输出扭矩的影响
Figure 14. Effect of afterburning on output torque at 1800 r/min
图 15 2400 r/min时补燃对输出扭矩的影响
Figure 15. Effect of afterburning on output torque at 2400 r/min
表 1 航空活塞发动机规格
Table 1. Specification for aviation piston engines
参数 数值 型式 水平对置2缸、增压、水冷 排量/L 0.4 冲程数 二冲程 缸径/mm 65.5 冲程 60 燃烧方式 缸内直喷 燃烧室形状 浅盆型燃烧室 压缩比 16 喷油系统 电控直列泵 额定转速/（r/min） 2400 扫气方案 气口横流扫气 喷孔数×喷孔直径/mm 4×0.18 油束夹角/（°） 150 喷油器倾斜角度/（°） 10 扫气开始角度/℃A 125 排气开始角度/℃A 110 注：表中℃A为曲轴转角 
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表 2 不同转速下边界条件的设置
Table 2. Setting of boundary conditions at different rotational speeds
变量 N=1800 r/min N=2400 r/min min max min max 进气压力/（105 Pa） 0.54 1 0.54 1 进气温度/K 255 298 255 298 空燃比 15 25 15 25 气缸峰值温度/K 1600 2200 1600 2200 气缸峰值压力/MPa 0 12 0 12 压力升高率/（MPa·℃A−1） 0 0.5 0 0.5
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表 3 不同发动机转速下两个工况点运行参数
Table 3. Operating parameters at two operating points at different engine speeds
工况点 N=1800 r/min N=2400 r/min A B A B 环境压力/kPa 100 100 100 100 空燃比 41.2 24 41.95 32.8 峰值温度/K 1276 1662 1880 1930 峰值压力/MPa 3.117 4.444 4.339 3.982 输出扭矩/（N·m） 11.56 23.37 23.04 26.38 BSFC/（g/（kw·h）） 297 245 248.6 245.87 平均有效压力/MPa 0.286 0.475 0.358 0.409
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表 4 每个发动机转速下三个工作点的补燃计算总结
Table 4. Summary of afterburning calculations for three operating points at each engine speed
工况点 N=1800 r/min N=2400 r/min A B A B 气缸循环喷油量/mg 5 8 5 6 进气歧管流量/（g/s） 8.56 7.67 8.85 9.11 废气中空气流量/（g/s） 6.42 4.23 5.99 5.68 初始废气温度/K 621 678 678 723 补燃50% 补燃流量/（g/s） 0.22 0.14 0.21 0.2 温度提升/K 136 36 152 110 新废气温度/K 757 714 830 833 补燃100% 补燃流量/（g/s） 0.44 0.28 0.42 0.4 温度提升/K 197 122 184 142 新废气温度/K 818 800 862 865
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表 5 航空活塞发动机在不同海拔下的特性参数
Table 5. Characteristic parameters of aviation piston engines at different altitudes
转速 N=1800 r/min N=2400 r/min 海拔/m 0 3000 5000 0 3000 5000 排气质量流量/（g/s） 14.9 10.7 8.3 16.0 11.1 76.3 环境压力/kPa 100 69 53 100 69 53 环境温度/K 288 268 255 288 268 255 扭矩/（N·m） 22.7 19.3 13.4 21.8 17.1 10.5 功率/kW 4.28 3.65 2.5 5.48 4.30 2.65
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