郑州航空工业管理学院学报

为解决燃气轮机高温涡轮叶片承受较高热负荷问题，以燃气涡轮径向内冷叶片为研究对象，采用气热耦合数值模拟方法，系统分析了叶片内部冷却通道的流动与传热特性。基于Fluent软件对带10个径向冷却通道的MarkⅡ型涡轮叶片进行仿真计算，验证了计算模型的可靠性，并重点探究了V形肋片结构对冷却通道传热特性的影响规律。研究结果表明：V形肋片结构可有效提升冷却通道的冷却效果和叶片的温度分布均匀性，与无肋片的光滑冷却通道相比，平均努塞尔数提升了35.6%；在冷却通道中布置V形肋片，当肋片冲击角为45度时，对涡轮叶片的冷却效果最优。

To solve the problem that high-temperature gas turbine blades bear the excessive thermal loads, this study investigates radially internally cooled gas turbine blades using a conjugate heat transfer numerical simulation approach and systematically analyzes the flow and heat transfer characteristics within the internal cooling passages of the blades. Numerical simulations are performed on a Mark II turbine blade comprising ten radial cooling channels using ANSYS Fluent software. The reliability of the computational model is validated. The study particularly examines the influence of V-shaped rib structures on the heat transfer performance of the cooling passages. The results demonstrate that V-shaped ribs significantly enhance the overall cooling performance of the cooling passages and improve the temperature distribution uniformity across the blade surface. Compared to smooth cooling passages without ribs, the average Nusselt number of passages with V-shaped ribs increases by 35.6%. Furthermore, it is found that among the V-shaped rib arrangements, the ribs with an attack angle of 45° provide the optimal cooling performance for the turbine blades.