Abstract
Axial slot casing treatment is a common method to extend the stall margin of a compressor. Based on the mechanism of unsteady flow control, this paper redesigns axial slots with large circumferential interval and small opening area. To test the effect of this axial slot structure, unsteady numerical simulations were carried out with different slot areas and circumferential intervals. The results show that this novel axial slot casing treatment can significantly improve compressor stall margin. Meanwhile, compared with the traditional axial slot, the efficiency loss is greatly reduced. The flow field analysis shows that the new axial slot structure proposed in this paper can suppress the development of tip leakage vortex and unsteadiness in the tip region at the near stall condition through decreasing the tip loading periodically. Moreover, we find that the slot area is proportional to the improvement of stability margin. Under the same slot area, an excessive number of slots is not conducive to the improvement of the stability margin.
Highlights
Circumferential Interval and SmallAs the loading of the compressor/fan increases, the stability problem becomes more and more prominent, which seriously restricts the development of high-performance aeroengines [1]
In orderial to slot improve the flow field and the stability margin effectively, traditional axcasing treatments often use a large number of slots and a very large slot areaslot to achieve often a largeuse amount momentum exchange between fluid and low-energy ial slot casing treatments a largeofnumber of slots and a veryhigh-energy large slot area fluid
This paper proposes a novel axial slots casing treatment structure with a large circumferential interval and small opening area
Summary
As the loading of the compressor/fan increases, the stability problem becomes more and more prominent, which seriously restricts the development of high-performance aeroengines [1]. Some flow control methods are needed to enhance the stability margin of the compressor to meet the requirements of high-performance engines [2]. Since most instability phenomena firstly occur at the tip of the blade, some casing treatment structures can improve the stability margin effectively through influencing the tip flow field. Among those casing treatment methods, axial slot structures are widely used because of their remarkable effect of extending the stall margin of the compressor. Wilke and Kau [3] conducted numerical simulations on a transonic compressor for a mechanism that improved the stall margin by using axial slots
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