Numerical investigation on effect of aspect ratio of axisymmetric circumferential groove casing treatment coupled to a transonic axial flow compressor stage

Mehta, JN and Alone, DB and Choksi, HS (2015) Numerical investigation on effect of aspect ratio of axisymmetric circumferential groove casing treatment coupled to a transonic axial flow compressor stage. In: ASME 2015 Gas Turbine India Conference, India.

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Abstract

While the effects of axisymmetric casing treatment on performance of an axial compressor stage have been extensively studied numerically as well as experimentally, the major geometrical parameters which govern these effects have been identified. Studies are now focused on understanding how each of these parameters individually impacts the performance of a casing treatment. The present work aims to study the impact on performance of casing treatment geometry when aspect ratio of the grooves is varied in a circumferential groove casing treatment. The compressor geometry chosen for this study has design characteristics of a transonic compressor stage. Flow field solutions were derived for baseline model by solving steady state 3-D Reynolds-Averaged Navier-Stokes (RANS) equations for three grid densities and the grid independence was proved. The basic casing treatment geometry has 10 circumferential grooves of width 4mm and axial spacing of 2mm between each groove. The aspect ratio was varied by changing the depth of the grooves in each case. These casing treatment geometries were superimposed over the rotor domain with the grooves extending over the entire blade tip chord and flow field solutions were again obtained for various aspect ratios of grooves. These results depict improvement in the range of operation in terms of mass flow rate. Results also show that the aspect ratio of the grooves significantly influences the overall effectiveness of casing treatment on the performance of compressor stage. Improvement in overall compressor efficiency is noted with lower aspect ratio casing treatments when compared to those with higher aspect ratios, however, the range improvement is higher with higher aspect ratios. It is also observed that, after a certain depth of grooves is reached, there is no significant improvement in performance on further increasing the depth and hence the aspect ratio. Post processing results of the flow solutions are presented which confirm the trends and show that the flow behavior near rotor tip governs this effect.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Aspect ratio; Casing treatment; Circumferential grooves; Transonic compressor
Subjects: AERONAUTICS > Aircraft Propulsion and Power
Depositing User: Mr. BS Shivaram
Date Deposited: 03 May 2018 09:15
Last Modified: 03 May 2018 09:15
URI: http://nal-ir.nal.res.in/id/eprint/12590

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