Abstract
Modern axial compressors demand high performance and increased operating range. High performance is generally obtained by employing 3D design features, such as sweep and lean. To improve operating range, use of circumferential casing grooves is quite common. An extensive numerical study is carried out to understand performance change due to swept rotor blade on axial compressor performance and stall margin, in the presence of circumferential casing grooves. Numerical methodology used in the current work is validated with experimental data of NASA Rotor37. Grid sensitivity as well as turbulence model validation is carried out to validate numerical methodology used in this work. A baseline rotor is created without any sweep. Sweep considered in this study is employed only at part span of the blade. Impact of part sweep with circumferential casing grooves is not reported by many in open literature, which is the focus of this work. Different magnitudes of sweep are considered in this study. The current study indicates existence of an optimum combination of magnitude of sweep and span location at which sweep starts from. Sweep in the presence of circumferential grooves results in considerable increase of operating range with nominal decrease in efficiency. A detailed flow field investigation is presented to understand the underlying flow physics.
Similar content being viewed by others
Abbreviations
- A :
-
area [\({\hbox {m}}^{2}\)]
- Ch :
-
chord length
- Mc :
-
corrected mass flow rate [kg/s]
- M, m :
-
physical mass flow rate [kg/s]
- PR :
-
ratio of total pressure at outlet to that at inlet
- \({\textit{PT}}_{\textit{in}}\) :
-
inlet total pressure [kPa]
- \({\textit{PT}}_{\textit{out}}\) :
-
outlet total pressure [kPa]
- TR :
-
ratio of total temperature at outlet to that at inlet
- \({\textit{TT}}_{\textit{in}}\) :
-
inlet total temperature [K]
- \({\textit{V}}_{\mathrm{m}}\) :
-
meridional velocity [m/s]
- \(\gamma \) :
-
ratio of specific heats
- \(\phi \) :
-
any variable
- \(\overline{\phi }\) :
-
average value of variable
- \({}_{\mathrm{stall}}\) :
-
properties corresponding to stall point
- \({}_{\mathrm{OP}}\) :
-
properties corresponding to operating point
- \(\lambda \) :
-
sweep magnitude
- \(\rho \) :
-
density [\({\hbox {kg/m}}^{3}\)]
References
Breugalmans F 1987 Investigation of dihedral effects in compressor cascades. AGARD-CP-421, Massachusetts
Sasaki T and Breugalmans F 1997 Comparison of sweep and dihedral effects on compressor cascade performance. J. Turbomach. 120: 454–463
Inoue M, Kuroumaru M, Furukawa, M, Kinoue Y, Tanino T, Maeda S and Okuno K 1997 Controlled-Endwall-Flow blading for multistage axial compressor. In: Proceedings of the International Gas Turbine and Aeroengine Congress and Exhibition, vol. 1, p. V001T03A044, https://doi.org/10.1115/97-GT-248
Godwin W R 1957 Effect of sweep on performance of compressor blade sections, as indicated by swept-blade rotor, unswept-blade rotor and cascade tests. Report NACA-TN-4062
Wadia A R, Szucs P N and Crall D W 1998 Inner workings of aerodynamic sweep. J. Turbomach. 120: 671–682
Choi K J, Kim J H and Kim K Y 2010 Design optimization of circumferential casing grooves for a transonic axial compressor to enhance stall margin. In: Proceedings of ASME GT 2010, vol. 7, pp. 687–695, https://doi.org/10.1115/GT2010-22396
Ramakrishna P V and Govardhan M 2009 Study of sweep and induced dihedral effects in sub-sonic axial flow compressor passages—part 1: design considerations—changes in incidence, deflection and streamline curvature. Int. J. Rotating Mach. 2009, https://doi.org/10.1155/2009/787145
Biollo R and Benini E 2008 Aerodynamic behaviour of a novel three-dimensional shaped transonic compressor rotor blade. In: Proceedings of ASME GT 2008, vol. 6, pp. 695–706, https://doi.org/10.1115/GT2008-51397
Bailey E E 1972 Effect of grooved casing treatment on the flow range capability of a single-stage axial-flow compressor. Report NASA\_TM\_X\_2459
Urasek D C, Lewis Jr. G W and Moore R D 1976 Effect of casing treatment on performance of an inlet stage for a transonic multistage compressor. Report NASA\_TM\_X\_3347
Lin F, Ning F and Liu H 2008 Aerodynamics of compressor casing treatment—part I: experiment and time-accurate numerical simulation. In: Proceedings of ASME GT 2008, vol. 6, pp. 731–744, https://doi.org/10.1115/GT2008-51541
Khan J A, Parvez K, Ahmad S and Mushtaq A 2011 Effect of circumferential grooves and tip recess on stall characteristics of transonic axial compressor rotor. In: Proceedings of the 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, https://doi.org/10.2514/6.2011-743
Reid L and Moore R D 1978 Design and overall performance of four highly loaded, high-speed inlet stages for an advanced high-pressure-ratio core compressor. Report NASA TP 1337
Reid L and Moore R D 1980 Experimental study of low aspect ratio compressor blading. J. Eng. Power 104: 875–882, https://doi.org/10.1115/1.3230353
Hah C and Reid L 1992 A viscous flow study of shock–boundary layer interaction, radial transport and wake development in a transonic compressor. J. Turbomach. 114: 538–547, https://doi.org/10.1115/1.2929177
Suder K L and Celestina M L 1996 Experimental and computational investigation of the tip clearance flow in a transonic axial compressor rotor. J. Turbomach. 118: 218–229, https://doi.org/10.1115/1.2836629
Hah C and Loellbach J 1999 Development of hub corner stall and its influence on the performance of axial compressor blade rows. J. Turbomach. 121: 67–77, https://doi.org/10.1115/1.2841235
Chima R V 1998 Calculation of tip clearance effects in a transonic compressor rotor. J. Turbomach. 121: 131–140, https://doi.org/10.1115/1.2841374
Gerolymos G A and Vallet I 1999 Tip-clearance and secondary flows in a transonic compressor rotor. J. Turbomach. 121: 751–762, https://doi.org/10.1115/1.2836729
Yamada K, Furukawa M, Nakano T, Inoue M and Funazaki K 2004 Unsteady three-dimensional flow phenomena due to breakdown of tip leakage vortex in a transonic axial compressor rotor. In: Proceedings of ASME GT 2004, pp. 515–526, https://doi.org/10.1115/GT2004-53745
Goswami S N and Govardhan M 2016 Effect of sweep on performance of an axial compressor with casing grooves. In: Proceedings of ASME GT 2016, p. V02AT37A004, 10 pp., https://doi.org/10.1115/GT2016-56045
Ansys CFX®15.0 User Manuals
Huang X, Chen H and Fu S 2008 CFD investigation on the circumferential grooves casing treatment of transonic compressor. In: Proceedings of ASME GT 2008, pp. 581–589, https://doi.org/10.1115/GT2008-51107
Huang X, Chen H, Ke S and Fu S 2010 An analysis of the circumferential grooves casing treatment for transonic compressor flow. Sci. China Phys. Mech. Astron. 53(2): 353–359, https://doi.org/10.1007/s11433-010-0123-0
Acknowledgements
Authors hereby take this opportunity to thank Honeywell Technology Solutions, Bangalore, India, for allowing this research work to be published.
Author information
Authors and Affiliations
Corresponding author
Rights and permissions
About this article
Cite this article
Goswami, S.N., Govardhan, M. Effect of part sweep on axial flow compressor performance in the presence of circumferential casing grooves. Sādhanā 44, 193 (2019). https://doi.org/10.1007/s12046-019-1176-z
Received:
Revised:
Accepted:
Published:
DOI: https://doi.org/10.1007/s12046-019-1176-z