Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

Ky-Quang Pham; Xuan-Truong Le; Cong-Truong Dinh

doi:10.15282/jmes.14.4.2020.05.0579

Authors

Ky-Quang Pham School of Excellent Education, Vietnam Maritime University, 484, Lach Tray Street, Le Chan District, Hai Phong City, 840225, Vietnam
Xuan-Truong Le Aeronautical and Space Engineering Department, Hanoi University of Science and Technology, 1, Dai Co Viet Road, Hai Ba Trung District, Hanoi, 100000, Vietnam
Cong-Truong Dinh Aeronautical and Space Engineering Department, Hanoi University of Science and Technology, 1, Dai Co Viet Road, Hai Ba Trung District, Hanoi, 100000, Vietnam. Phone: +842438682525; Fax: +842438684945

DOI:

https://doi.org/10.15282/jmes.14.4.2020.05.0579

Keywords:

Transonic axial compressor, stator splitter blades, RANS analysis, total pressure ratio, adiabatic efficiency, stall margin, stable range extension

Abstract

Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.

References

R. K. Bhargava and G. Gopalakrishnan, “Optimising Splitter Vane Locations Using the Method of Singularities,” 1978.

J. Fabri, “Flow Distribution in a Radial Impeller with Splitter Vanes,” 1978.

T. Ogawa and G. Gopalakrishnan, “Use of Splitter Vanes in Centrifugal Compressor Impellers,” 1981.

M. Oana, O. Kawamoto, H. Ohtani and Y. Yamamoto, “Approach to High Performance Transonic Centrifugal Compressor,” 2002, doi: 10.2514/6.2002-3536.

G. Kergourlay, M. Younsi, F. Bakir and R. Rey, “Influence of Splitter Blades on the Flow Field of a Centrifugal Pump: Test-Analysis Comparison,” Int. J. Rotating Mach. Vol. 2007, vol. 2007, pp. 1–13, 2007, doi: 10.1155/2007/85024.

N. Madhwesh, K. V. Karanth and N. Y. Sharma, “Impeller Treatment for a Centrifugal Fan using Splitter Vanes – A CFD Approach,” in Proceedings of the World Congress on Engineering 2011, 2011, pp. 1981–1986.

A. J. Wennerstrom and G. R. Frost, “Design of a Rotor Incorporating Splitter Vanes for a High Pressure Ratio Supersonic Axial Compressor Stage,” Aerosp. Res. Lab. Rep. ARL 74-0110, 1974.

K. L. Tzuoo, S. S. Hingorani and A. K. Sehra, “Design Methodology for Splittered Axial Compressor Rotors,” 1990, doi: 10.1115/90-GT-066.

H. Li, Z. Zou and H. Liu, “Flow Analysis of a Single-stage Axial Compressor with a Splitter Rotor,” in Proceedings of ASME Turbo Expo 2004: Power for Land, Sea and Air, 2004, pp. 365–373, doi: https://doi.org/10.1115/GT2004-53265.

S. Drayton, “Design, Test, and Evaluation of a Transonic Axial Compressor Rotor with Splitter Blades,” Naval Postgraduate School, Monterey, California, USA, 2013.

L. Reid and R. D. Moore, “Design and Overall Performance of Four Highly Loaded, High-Speed Inlet Stages for an Advanced High-Pressure-Ratio Core Compressor,” NASA Tech. Pap., vol. 1337, 1987.

J. H. Kim, K. J. Choi and K. Y. Kim, “Optimization of a Transonic Axial Compressor considering Interaction of Blade and Casing Treatment to Improve Operating Stability,” 2011, doi: 10.1115/GT2011-45404.

J. H. Kim, K. J. Choi and K. Y. Kim, “Aerodynamic analysis and optimization of a transonic axial compressor with casing grooves to improve operating stability,” Aerosp. Sci. Technol., vol. 29, no. 1, pp. 81–91, 2013, doi: 10.1016/j.ast.2013.01.010.

J. H. Kim, D. W. Kim, and K. Y. Kim, “Aerodynamic optimization of a transonic axial compressor with a casing groove combined with tip injection,” Proc. Inst. Mech. Eng. Part A J. Power Energy, vol. 227, no. 8, pp. 869–884, 2013, doi: 10.1177/0957650913503311.

C. T. Dinh and K. Y. Kim, “Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor,” Int. J. Turbo Jet-Engines, vol. 36, no. 3, pp. 283–296, 2019, doi: 10.1515/tjj-2016-0077.

C. T. Dinh, M. W. Heo and K. Y. Kim, “Aerodynamic performance of transonic axial compressor with a casing groove combined with blade tip injection and ejection,” Aerosp. Sci. Technol., vol. 46, pp. 176–187, 2015, doi: 10.1016/j.ast.2015.07.006.

C. T. Dinh, S. B. Ma and K. Y. Kim, “Effects of a Circumferential Feed-Back Channel on Aerodynamic Performance of a Single-Stage Transonic Axial Compressor,” 2017, doi: 10.1115/GT201763536.

C. T. Dinh, S. B. Ma and K. Y. Kim, “Aerodynamic Optimization of a Single-Stage Axial Compressor with Stator Shroud Air Injection,” AIAA J., vol. 55, no. 8, pp. 2739–2754, 2017, doi: 10.2514/1.J055909.

C. T. Dinh, D. Q. Vu and K. Y. Kim, “Effects of Rotor Bleeding Airflow on Aerodynamic and Structural Performances of a Single-stage Transonic Axial Compressor,” Int. J. Aeronaut. Sp. Sci., vol. 21, no. 3, pp. 599–611, 2020, doi: 10.1007/s42405-019-00239-5.

K. Q. Pham, Q. H. Nguyen, T. D. Vuong and C. T. Dinh, “Parametric Study on Aerodynamic Performance of a Single-stage Transonic Axial Compressor with Recirculation-bleeding Channels,” Int. J. Fluid Mach. Syst., vol. 13, no. 2, pp. 348–360, 2020, doi: 10.5293/IJFMS.2020.13.2.348.

ANSYS CFX-19.1., “Theory Guide 2018.” ANSYS, Inc., Hanoi, Vietnam, 2018.

H. Chen, X. D. Huang and S. Fu, “CFD Investigation on Stall Mechanisms and Casing Treatment of a Transonic Compressor,” in 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2006, pp. 4789–4798, doi: 10.2514/6.2006-4799.