Design and optimization of dual resonance tube exhaust system for aviation piston engines
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摘要:
二冲程活塞发动机常采用涡轮增压耦合排气谐振技术解决其高空吸气难题，但对于四缸发动机，排气谐振系统中同相位排气引起的废气阻滞与压力干涉会导致高空性能恶化。因此基于废气压力波传递理论与遗传算法，设计并优化了双谐振管排气系统，并通过三维流体动力学仿真验证，证明了双谐振管排气系统解决废气阻滞与压力干涉问题的同时有效利用压力波优化排气背压分布。仿真优化结果表明：采用双排气谐振系统的发动机在海拔
5000 m内条件下实现维持原机功率并略有提升。在5000 m以上的大部分高海拔条件下，优化后功率较原机提高5%以上，且提升幅度随海拔升高而增大，在10000 m的高海拔条件下，功率提升最高达到34.7%。研究证实双谐振管排气系统可以有效解决四缸机多缸同相位排气出现的废气阻滞与压力干涉问题。Abstract:Two-stroke piston engines often employ turbocharging coupled with exhaust resonance technology to address air intake challenges at high altitudes. However, for four-cylinder engines, exhaust gas blocking and pressure interference caused by in-phase exhaust in the exhaust resonance system lead to performance degradation at high altitudes. Therefore, a dual resonance tube exhaust system was designed and optimized based on the exhaust pressure wave propagation theory and a genetic algorithm. Three-dimensional fluid dynamics simulations were conducted to verify that the dual resonance tube exhaust system solved the problem of exhaust gas blocking and pressure interference while effectively utilizing pressure waves to optimize the exhaust backpressure distribution. The simulation and optimization results showed that the engine equipped with the dual exhaust resonance system maintained the original power and achieved a slight increase under conditions up to an altitude of
5000 m. Under most high-altitude conditions above5000 m, the optimized power increased by more than 5% compared with the original engine, and the improvement increased with altitude. At a high altitude of 10 000 m, the maximum power increase reached 34.7%. The study confirmed that the dual resonance tube exhaust system can effectively solve the problems of exhaust gas blocking and pressure interference caused by in-phase exhaust in a four-cylinder engine. -
图 1 发动机原始谐振增压系统示意图
Figure 1. Schematic diagram of the original resonant supercharging system of the engine
图 2 双谐振管排气谐振增压系统示意图
Figure 2. Schematic diagram of the dual resonance tube exhaust pressurization system
图 12 基于遗传算法的排气谐振系统优化设计方法示意图
Figure 12. GA-based optimization methodology schematic diagram of exhaust resonant systems
图 16 不同海拔条件下优化前后发动机功率变化
Figure 16. Variation in engine power before and after optimization under different altitude conditions
图 17 0 m与
5000 m海拔条件下优化前后排气背压变化Figure 17. Comparison of exhaust backpressure at 0 m and 5000 m altitude before and after optimization
图 18 不同海拔优化前后捕获率的对比
Figure 18. Comparison of capture rate before and after optimization at different altitudes
图 19 0 m与
5000 m海拔条件下优化前后歧管压力曲线Figure 19. Manifold pressure curves at 0 m and
5000 m altitude before and after optimization
图 20 整流歧管排气阶段压力云图
Figure 20. Pressure contour plot of the collecting manifold during exhaust phase
图 21 歧管段内压力干涉与废气滞留示意图
Figure 21. Schematic diagram of pressure interference and exhaust gas retention in manifold section
图 22 排气谐振管内换气阶段压力云图
Figure 22. Pressure contours during gas exchange phase within the exhaust resonator
图 23 排气谐振管内换气阶段流速云图
Figure 23. Velocity contours during gas exchange phase within the exhaust resonator
表 1 发动机参数
Table 1. Engine specifications
参数 数值及说明 发动机型式 水平对置，四缸，二冲程 排量/L 1.35 缸径/mm 82 冲程/mm 64 额定转速/（r/min） 6000 压缩比 8.0 供油方式 空气辅助缸内直喷 曲轴转角/（°） 排气口开启 87 排气口关闭 273 扫气口开启 123 扫气口关闭 237 
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表 2 排气谐振系统符号说明
Table 2. Nomenclature of the exhaust resonance system
符号 说明 符号 说明 Lm 排气歧管长度 L4 收缩段长度 Le 扩张段位置 L5 出口段长度 Lt 收缩段位置 D1 入口直径 L1 入口段长度 D2 扩张直径 L2 扩张段长度 D3 出口直径 L3 等径段长度
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表 3 排气谐振管主要结构参数
Table 3. Tuned exhaust pipe structure parameters
mm 参数 数值 参数 数值 Lm 137 L4 200 Le 545 L5 40 Lt 1245 D1 55 L1 147 D2 120 L2 398 D3 40 L3 500
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表 4 谐振管参数优化范围
Table 4. Optimization range for resonator parameters
mm 参数 数值 参数 数值 $ {L}_{\text{e}} $ 200～500 $ {L}_{3} $ 100～500 $ {L}_{\text{t}} $ 800～ 1200 $ {L}_{4} $ 100～400 $ {L}_{1} $ 200～300 $ {D}_{2} $ 60～90 $ {L}_{2} $ 0～500 $ {D}_{3} $ 35～50
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表 5 谐振管参数优化结果
Table 5. Optimization results of tuned tube parameters
mm 参数 数值 参数 数值 Le 498 L3 476 Lt 1100 L4 126 L1 299 $ {D}_{2} $ 89 L2 179 $ {D}_{3} $ 35
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