Optimization of a circumferential groove in a centrifugal compressor
-
Myong Hun Oh
Abstract
In this work, a circumferential groove on the shroud was applied to a centrifugal compressor and optimized to improve the stability of the compressor. To reduce the number of design variables before optimization, the position of the casing groove that maximizes the stall margin of the compressor was firstly selected. The width and height of the casing groove were optimized using the RSM (Response Surface Method) and the full factorial design of experiments to increase the stall margin further. It was observed that the optimized case with the casing groove can increase the stall margin by 7.0% but the adiabatic efficiency at the design condition decreases by 0.99%, in comparison to the reference case without the groove. Finally, the flow field of both cases with and without the optimized casing groove was compared to each other to analyze effects of the casing groove on the stall margin and design efficiency. The casing groove decreases the leakage flow across the impeller tip and weakens the tip leakage vortex, consequently decreasing the blockage near the shroud and improving the stall margin. However, it was found that the spillage of the flow from the casing groove increases the mixing loss near the shroud.
Funding source: 2018 Research Fund of Myongji University
-
Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
-
Research funding: This work was supported by 2018 Research Fund of Myongji University.
-
Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Wiseler, DC, Beacher, BF. Improved compressor performance using recessed clearance (trenches). J Propul Power 1989;5:469–75.10.2514/3.23178Search in Google Scholar
2. Shabbir, A, Addamczyk, JJ. Flow mechanism for stall margin improvement due to circumferential casing grooves on axial compressors. J Turbomach 2005;127:708–17. https://doi.org/10.1115/1.2008970.Search in Google Scholar
3. Kim, JH, Choi, KJ, Husain, A, Kim, KY. Multiobjective optimization of circumferential casing grooves for a transonic axial compressor. J Propul Power 2011;27:730–3. https://doi.org/10.2514/1.50563.Search in Google Scholar
4. Kim, JH, Choi, KJ, Kim, KY. Performance evaluation of a transonic axial compressor with circumferential casing grooves. P I Mech Eng A – J Power Energy 2011;226:218–30. https://doi.org/10.1177/0957650911427244.Search in Google Scholar
5. Houghton, T, Day, I. Enhancing the stability of subsonic compressor using casing grooves. J Turbomach 2011;133:021007. https://doi.org/10.1115/1.4000569.Search in Google Scholar
6. Heinichen, F, Gümmer, V, Schiffer, H-P. Numerical investigation a single circumferential groove casing treatment on three different compressor rotors. ASME Paper GT2011-45905, 2011.10.1115/GT2011-45905Search in Google Scholar
7. Sakuma, Y, Watanabe, T, Himeno, T, Kato, D, Murooka, T, Shuto, Y. Numerical analysis of flow in a transonic compressor with a single circumferential casing groove: influence of groove location and depth on flow instability. J Turbomach 2013;136:031017. https://doi.org/10.1115/1.4025575.Search in Google Scholar
8. Choi, M. Effects of circumferential casing grooves on the performance of a transonic axial compressor. Int J Turbo Jet Eng 2015;32:361–71. https://doi.org/10.1515/tjj-2015-0001.Search in Google Scholar
9. Chen, H, Huang, X, Fu, S. CFD investigation on stall mechanisms and casing treatment of a transonic compressor. AIAA Paper 2006-4799, 2006.10.2514/6.2006-4799Search in Google Scholar
10. Cumpsty, NA. Compressor aerodynamics. Florida, USA: KRIEGER; 2004.Search in Google Scholar
11. Rabe, DC, Hah, C. Application of casing circumferential grooves for improved stall margin in a transonic axial compressor. ASME Paper No. GT-2002-30641, 2002.10.1115/GT2002-30641Search in Google Scholar
12. Vo, HD, Tan, CS, Greitzer, EM. Criteria for spike initiated rotating stall. J Turbomach 2008;130:031017. https://doi.org/10.1115/1.2750674.Search in Google Scholar
13. Choi, M, Vahdati, M, Imregun, M. Effects of fan speed on rotating stall inception and recovery. J Turbomach 2011;133:041013. https://doi.org/10.1115/1.4003243.Search in Google Scholar
14. Choi, M, Smith, NHS, Vahdati, M. Validation of numerical simulation for rotating stall in a transonic fan. J Turbomach 2013;135:021004. https://doi.org/10.1115/1.4006641.Search in Google Scholar
© 2021 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC
- Effect of multi-hole arrangement on the effusion cooling with backward injection
- Research on a component characteristic adaptive correction method for variable cycle engines
- Optimization of a circumferential groove in a centrifugal compressor
- Comparative study of numerical approaches to adaptive gas turbine cycle analysis
- Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
- Experimental research on suppressing unbalanced vibration of rotor by integral squeeze film damper
- The influence of the geometry of V-gutter bluff body on transient vortex shedding
- Design and validation of a two-dimensional variable geometry inlet
- Computational assessment of performance parameters of an aero gas turbine combustor for full flight envelope operation
- Investigation of effect of atomization performance on lean blowout limit for gas turbine combustors by comparison of utilizing aviation kerosene and methane as fuel
- Design optimization of a supersonic through-flow fan rotor based on the blade profiles
Articles in the same Issue
- Frontmatter
- Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC
- Effect of multi-hole arrangement on the effusion cooling with backward injection
- Research on a component characteristic adaptive correction method for variable cycle engines
- Optimization of a circumferential groove in a centrifugal compressor
- Comparative study of numerical approaches to adaptive gas turbine cycle analysis
- Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
- Experimental research on suppressing unbalanced vibration of rotor by integral squeeze film damper
- The influence of the geometry of V-gutter bluff body on transient vortex shedding
- Design and validation of a two-dimensional variable geometry inlet
- Computational assessment of performance parameters of an aero gas turbine combustor for full flight envelope operation
- Investigation of effect of atomization performance on lean blowout limit for gas turbine combustors by comparison of utilizing aviation kerosene and methane as fuel
- Design optimization of a supersonic through-flow fan rotor based on the blade profiles
