氢内燃机两级增压系统协同匹配设计方法

    Coordinated Matching Design Method for Two-Stage Turbocharging System of Hydrogen Internal Combustion Engines

    • 摘要: 针对氢内燃机多级涡轮增压系统匹配优化设计难度高的问题,构建了基于涡轮增压器几何构型的两级增压氢内燃机的耦合性能仿真模型。首先,建立了叶轮机热力学过程和准维流动的涡轮和压气机性能预测模型,并将该模型与氢内燃机预测模型通过GT-Power与Simulink工具耦合,实现了氢内燃机与增压系统的性能耦合仿真预测。基于该仿真方法建立了两级增压系统关键几何参数与氢内燃机热效率的反向传播(back-propagation, BP)神经网络代理模型,并通过敏感性分析量化了增压系统关键几何参数对氢内燃机性能的影响权重。最后,基于该降阶模型并结合多目标优化算法,实现了氢内燃机两级增压系统关键几何参数协同优化匹配设计。协同优化结果表明:低压级压气机叶轮修整比值从50.96增大至59.50以扩大稳定运行范围,高压级涡轮喉口面积放大10%以提升排气能量回收效率,使压气机运行线精准落入高效区,4个研究工况有效热效率相对提升了0.88%~2.16%,燃氢消耗率降低0.63~1.60 g/(kW·h),泵气平均有效压力绝对值显著降低;同时,缸内最高燃烧压力降低1.12%~3.26%。该协同优化匹配设计的方法可实现多工况经济性与稳定性的协同提升。

       

      Abstract: To address the high complexity in matching and optimization design of multi-stage turbocharging systems for hydrogen engines, a coupled performance simulation model for two-stage turbocharged hydrogen engines based on turbocharger geometric configuration was constructed. Performance prediction models for turbines and compressors considering turbomachine thermodynamic processes and quasi-dimensional flow were established, and coupled with the hydrogen engine prediction model using GT-Power and Simulink, enabling coupled performance simulation and prediction of the hydrogen engine and turbocharging system. Based on the simulation method, a back-propagation(BP) neural network surrogate model between key geometric parameters of the two-stage turbocharging system and hydrogen engine thermal efficiency was developed, and sensitivity analysis was used to quantify the influence weights of key geometric parameters of the turbocharging system on engine performance. Finally, based on the reduced-order model combined with a multi-objective optimization algorithm, coordinated optimization and matching design of key geometric parameters for the two-stage turbocharging system were achieved. Coordinated optimization results indicate that the impeller trim ratio of the low-pressure stage compressor was increased from 50.96 to 59.50 to expand the stable operating range and the high-pressure stage turbine throat area was enlarged by 10% to improve the exhaust gas energy recirculation rate, positioning the compressor operating lines precisely within the high-efficiency zones. For the four operating conditions, the effective thermal efficiency showed a relative improvement of 0.88%~2.16%, the hydrogen consumption rate was reduced by 0.63~1.60 g/(kW·h) and the absolute value of pumping mean effective pressure(PMEP) markedly decreased. Meanwhile, the maximum in-cylinder combustion pressure was reduced by 1.12%~3.26%. This coordinated optimization method achieves synergistic improvements in multi-condition fuel economy and operational stability.

       

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