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CFD Analysis of Swept and Leaned Transonic Compressor Rotor

Author(s): Nivin Francis#1 , J. Bruce Ralphin Rose

Journal: International Journal of Engineering Trends and Technology
ISSN 2231-5381

Volume: 4;
Issue: 6;
Start page: 2524;
Date: 2013;
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Keywords: Transonic compressor | Shock interaction | Sweep and Lean | Boundary layer

For an axial compressor, to increase the pressure rise per stage, it is necessary to increase the blade speed and provide high deflection to fluid. Increasing the blade speed springs up the formation of transonic compressor, which has a lot of advantages, such as reduction in weight, cost, and noise etc. The pressure rises in transonic compressor are mostly through shock diffusion. But the shock interacts with phenomenon such as boundary layer, secondary flows, and tip leakage vortex creating instability to the compressor. The shock interaction reduces the efficiency, such that it is lesser than that produced by a subsonic one. The shock interaction, also limits the working range of transonic compressor. So by changing the shock position the stability can be increased. The improvements in compressor performance can be done with several techniques such sweep, lean, casing treatments, air ingestion and bleeding. Several computational and experimental analyses have been done by providing sweep and lean techniques alone and achieved good results. Here sweep and lean in a combined mode is applied on Rotor 35, an experimental model of transonic compressor built by NASA, and analysed computationally. The results are compared and found improvements.
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