发表机构
School of Aeronautics and Astronautics, Shanghai Jiao Tong University; Wuhan Second Ship Design and Research Institute（上海交通大学航空航天学院; 武汉第二船舶设计研究所）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
本文提出一种广义混合平面方法，通过嵌套压力根搜索与焓反演算法处理可压缩反应流，实现整机涡轮机械模拟中热力学一致的界面耦合，误差低于0.11%。
AI 中文摘要
混合平面方法在多个涡轮机械部件的稳态模拟中起着关键作用。随着计算能力的进步，整机燃气轮机模拟不再是难以实现的方法。然而，整机模拟需要同时耦合压气机、涡轮和燃烧室。一个关键挑战是，燃烧室后的工质不能再被视为理想气体，因为燃烧引入了成分变化和燃烧产物。基于固定成分气体的传统混合平面方法无法保证热力学一致的混合输出状态。为克服这一困难，本文扩展了经典混合平面方法以处理可压缩反应流。热力学封闭中的非线性通过一种新颖的嵌套算法解决，该算法结合了外部压力根搜索与内部焓反演。引入了物理状态检查和幂律压力采样，以提高在压力根接近其物理上限的低法向速度下的数值鲁棒性。该方法的性能在三种配置中得到验证：准一维界面测试，阐明了所提出的混合平面公式对不同燃料类型和流动条件的热力学刚性；达姆施塔特跨声速压气机案例，验证了当混合分数降至零时，所提出的方法退化为经典混合平面公式；以及KJ66微型涡喷发动机的整机模拟，用于展示该方法在多物理场涡轮机械模拟中的性能。与实验数据吻合良好，混合平面上的最大相对质量流量误差保持在0.11%以下，证明了可压缩反应涡轮机械流动的守恒且热力学一致的界面耦合。
英文摘要
The mixing-plane method plays a pivotal role in steady simulations of multiple turbomachinery components. With advances in computational power, a whole-engine gas turbine simulation is no longer an elusive approach. However, whole-engine simulations require simultaneous coupling of the compressor, turbine and combustor. A key challenge is that the working fluid after the combustor can no longer be treated as a perfect gas, since the combustion introduces composition variations and combustion products. Conventional mixing-plane methods based on a fixed-composition gas cannot guarantee a thermodynamically consistent mixed-out state. To overcome the difficulty, this paper extends the classic mixing-plane approach to handle compressible reacting flows. The nonlinearity in the thermodynamic closure is addressed using a novel nested algorithm combining an outer pressure-root search with an inner enthalpy inversion. Physical state checks and power-law pressure sampling are incorporated to improve numerical robustness at low normal velocities where the pressure root approaches its upper physical bound. The performance of the method is demonstrated in three configurations: a quasi-1D interface test elucidating the thermodynamic stiffness of the proposed mixing-plane formulation for different fuel types and flow conditions; the Darmstadt transonic compressor case that verifies the proposed method reduces to the classic mixing-plane formulation when the mixture fraction reduces to zero; and a whole-engine simulation of the KJ66 micro-turbojet is used to demonstrate the performance of the method for multiphysics turbomachinery simulations. Good agreement with experimental data is observed, and the maximum relative mass-flow error across the mixing planes remains below 0.11%, demonstrating conservative and thermodynamically consistent interface coupling for compressible reacting turbomachinery flows.
