为了提升航空发动机总体性能计算模型的精度，提出一种主流热力循环与二次流流动融合的航空发动机总体性能计算模型建模方法。通过研究航空发动机总体性能计算原理，全面识别了二次流流动对主流热力循环的主要影响因子，揭示了二次流流动影响因子对主流热力循环影响的机理，并获取二次流流动对主流热力循环影响的特性。该方法在传统总体性能计算模型建模方法基础上，创新增加了二次流流量项、能量项及掺混项与主流热力循环的耦合计算。利用该方法完成了某发动机总体性能计算模型建模，结果表明，提出的改进总体性能建模方法较传统模型推力计算精度提升1.4%，耗油率计算精度提升1.33%，涡轮前温度计算精度提升2.7%，全面提升了航空发动机总体性能计算模型建模的精度。

To improve the calculation accuracy of the overall performance model， a overall performance modeling method for aero-engines with primary and secondary flow integration was investigated. Through research on principles for aero-engine performance calculation， the influencing factors of secondary flow on the primary flow thermodynamic cycle were comprehensively identified. Their mechanisms of action were clarified. A characteristic model of the impact of secondary flow on the primary flow thermodynamic cycle was constructed. Based on the traditional modeling framework， this method innovatively introduced a coupling calculation mechanism for secondary flow rate， energy， and mixing terms with the primary flow thermodynamic cycle. Using this method， an overall performance calculation model was developed for a specific aero-engine. The results show that， compared to traditional models， the proposed method achieves a 1.4% improvement in thrust calculation accuracy， a 1.33% enhancement in fuel consumption rate prediction， and a 2.7% increase in turbine inlet temperature estimation accuracy， significantly optimizing the precision of the overall performance calculation model for aero-engines.