Engine size and weight optimization have always been high-priority design objectives for designers. Compressors occupy a relatively large part of the gas turbine engine. Owing to the adverse pressure gradient in the compressor, achieving the required pressure ratio within fewer stages has been a challenging task for compressor designers. Tandem blading is one of the novel concepts, which could be used to increase the pressure ratio by means of higher flow turning through the blade passages. This paper presents the performance characteristics of a tandem stage based on results from experiments and numerical analyses. The investigation is further extended to analyze the effect of a radial hub and tip distortion on the performance of the tandem stage. The experimental results are very well supported with some interesting numerical results, particularly near the hub and tip region. It is observed that the tandem stage demonstrates higher pressure rise and stall margin under clean inflow. The tandem stage is also observed to be more sensitive to radial distortion leading to a significant loss in the total pressure and the stall margin.

发动机尺寸和重量优化一直是设计师优先考虑的设计目标。压缩机占据燃气涡轮发动机的较大部分。由于压缩机中存在不利的压力梯度，在较少的级数内实现所需的压力比一直是压缩机设计人员的一项具有挑战性的任务。串联叶片是一种新颖的概念，可用于通过更高的流量转向通过叶片通道来增加压力比。本文根据实验和数值分析的结果介绍了串联级的性能特征。该调查进一步扩展到分析径向轮毂和尖端变形对串联级性能的影响。实验结果很好地支持了一些有趣的数值结果，特别是在轮毂和尖端区域附近。观察到串联级在清洁流入下表现出更高的压力上升和失速裕度。还观察到串联级对径向变形更敏感，从而导致总压力和失速裕度的显着损失。