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Numerical Investigation of the Interaction between Mainstream and Tip Shroud Leakage Flow in a 2-Stage Low Pressure Turbine

ISSN号：1003-2169
期刊名称：《热科学学报：英文版》
时间：0
分类：TK172[动力工程及工程热物理—热能工程] V232.2[航空宇航科学与技术—航空宇航推进理论与工程;航空宇航科学技术]
作者机构：[1]National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, School of Energy andPower Engineering, Beihang University, Beijing 100191, China
相关基金：Financially supported by the Innovation Foundation of BUAA for PhD Graduates （YWF-13-A01-014）

作者： JIA Wei LIU Huoxing[1]

关键词：低压涡轮, 相互作用, 泄漏流, 数值研究, 顶罩, 空气动力学性能, 泄漏损失, 泄漏损耗, tip shroud, leakage flow, entropy rise, low pressure turbine, aerodynamic loss

中文摘要：

对先进煤气的汽轮机要求在一台汽轮机识别损失并且理解生产他们的物理机制的未来的紧迫的要求。在有笼罩的片的低压力汽轮机，这些损失的大部分被尖端笼罩漏流动产生并且联系了相互作用。为这个原因，笼罩漏损失通常被组织进漏流动本身的损失和在漏流动和主流之间的相互作用引起的损失。以便在汽轮机性能上评估笼罩漏流动和相关损失的影响，为 2 阶段的计算调查低压力汽轮机在这被介绍并且讨论纸。用混合飞机途径的三维的稳定的多级式的计算包括详细尖端笼罩几何学被执行。结果证明有笼罩的片的汽轮机以空气动力学的性能比 unshrouded 有一个明显的优点。当混合损失在第二个阶段统治时，损失机制故障分析证明漏损失是在第一个阶段的主要贡献者。由于 blade-to-blade 压力坡度，入口和出口洞介绍不一致的漏注射和抽取。在出口洞的流动充满洞旋涡，附在洞墙的漏喷气和主要流动摄取导致的再通行地区。而且，光线的差距和尖端笼罩的出口洞尺寸在主要流动在尖端区域附近在 yaw 角度上有主要效果。因此，笼罩漏流动的充分计算在几何特征需要在汽轮机设计过程期间被考虑的汽轮机表演分析和笼罩是必要的。

英文摘要：

The pressing demand for future advanced gas turbine requires to identify the losses in a turbine and to understand the physical mechanisms producing them. In low pressure turbines with shrouded blades, a large portion of these losses is generated by tip shroud leakage flow and associated interaction. For this reason, shroud leakage losses are generally grouped into the losses of leakage flow itself and the losses caused by the interaction between leak- age flow and mainstream. In order to evaluate the influence of shroud leakage flow and related losses on turbine performance, computational investigations for a 2-stage low pressure turbine is presented and discussed in this paper. Three dimensional steady multistage calculations using mixing plane approach were performed including detailed tip shroud geometry. Results showed that turbines with shrouded blades have an obvious advantage over unshrouded ones in terms of aerodynamic performance. A loss mechanism breakdown analysis demonstrated that the leakage loss is the main contributor in the first stage while mixing loss dominates in the second stage. Due to the blade-to-blade pressure gradient, both inlet and exit cavity present non-uniform leakage injection and extrac- tion. The flow in the exit cavity is filled with cavity vortex, leakage jet attached to the cavity wall and recircula- tion zone induced by main flow ingestion. Furthermore, radial gap and exit cavity size of tip shroud have a major effect on the yaw angle near the tip region in the main flow. Therefore, a full calculation of shroud leakage flow is necessary in turbine performance analysis and the shroud geometric features need to be considered during turbine design process.

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