Investigation on the Flow Structures in the Tip Region for a Transonic Axial Compressor Rotor

DOI

10.2991/icmemtc-16.2016.72How to use a DOI?

Keywords

transonic compressor; numerical simulations; tip leakage flow

Abstract

The effect of flow structures in the tip region on the stability of NASA Rotor 37 has been examined with numerical simulation. Stall inception mechanism of Rotor 37 is presented firstly with principal focus on the tip leakage flow behavior, passage shock wave and leakage flow vortex. Detailed survey reveals three features: (1) there exists an interface between the incoming main flow and the tip leakage flow;(2) in this rotor, the tip leakage flows along the blade chord can be divided into at least three parts, each part plays a different role in the tip region;(3) the combined interaction of the stagnated blockage due to breakdown of the leakage vortex and the leakage flow from the leading edge leads to the tip stall inception. When flow and tip leakage flow intersect with each other, there is great rivalry between the two flows. If the power of incoming flow is relatively large, the flow will be coerced a lot of tip clearance leakage flow smoothly into the passage. And vortex breakdown would not have happened to produce large numbers of low-energy groups. And after the "collision" of the incoming flow, the secondary tip clearance flow will be greatly reduced. The efficiency of compressor will rise. Conversely, if the power of incoming flow is relatively small, tip part of the clearance leakage flow will be enveloped into the blade passage by main flow. But this part is unable to be taken out of the blade passage, and the collision of the two weakens their respective power further more. Under the influence of reverse pressure gradient, the vortex breakdown and low energy mass blockage escalate. As a result of the gradually decreasing power of the incoming flow, the secondary tip clearance flow get emerging. Thus the interface moves forward and spill out of blade passage from leading edge.

Copyright

© 2016, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Tianye Ji
AU  - Xie Fang
AU  - Youjun Wang
AU  - Tao Yi
PY  - 2016/04
DA  - 2016/04
TI  - Investigation on the Flow Structures in the Tip Region for a Transonic Axial Compressor Rotor
BT  - Proceedings of the 2016 3rd International Conference on Materials Engineering, Manufacturing Technology and Control
PB  - Atlantis Press
SP  - 373
EP  - 379
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmemtc-16.2016.72
DO  - 10.2991/icmemtc-16.2016.72
ID  - Ji2016/04
ER  -