Aerothermodynamics

Effect of Geometric Variation of Root Fillet on the Flow Characteristic of a Transonic Compressor Rotor

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  • 1. College of Civil Engineering and Architecture, Shandong University of Science and Technology, Qingdao 266590, China
    2. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
    3. Clean energy laboratory, Shandong University of Science and Technology, Qingdao 266590, China
    4. Key Laboratory of Aerodynamic Thermophysics of Shandong Province, Qingdao Institute of Aeronautical Technology, Qingdao 266400, China

Online published: 2023-11-11

Supported by

This research work was sponsored by the Youth Fund of National Natural Science Foundation of China (Grant No.51906243), the General Program of National Natural Science Foundation of China (Grant No.52076124) and the General Program of Natural Science Foundation of Shandong Province (Grant No. ZR2020ME173).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023

Abstract

The effects of root fillet on the flow behavior of high loading compressor rotor tends to be much more crucial in practice, and it’s necessary to explore the internal relations between the geometric effects of root fillet and the flow behaviors of rotor blade. Therefore, eight types of root fillet with different radius were designed and installed around the blade root of NASA Rotor67. With the aids of fillet, the corner separation near suction side of blade root has been suppressed significantly in that the root fillet reconstructs the circumferential bending distributon of the suction-side curve from leading edge to trailing edge, and reduces the genmetric turning angle in the latter part of root section near trailing edge. However, apart from the improvement of corner flow characteristic caused by root fillet, both the tip flow deterioration and the decrease of stall margin occur in the new rotors, which indicates an indirect correlation between tip flow characteristic and root fillet exists indeed in the three-dimensional flowfields of transonic rotor. Actually, by means of the new radial pressure equilibrium affected by root fillet, a larger radius of root fillet contributes to much larger blade loading and stronger leakage flow in tip region of compressor rotor. As a result, a monotonic decrease of stall margin was present in the transonic rotor with increase of the root fillet radius. Subsequently, the positive bending of blade tip was introduced to deal with the negative effect caused by the root fillet indirectly. Combined with the effects of root fillet and positive tip-bending on the radial pressure equilibrium existing in channels, both the radial and streamwise loading distributions tend to be much more reasonable in new rotors, and the static pressure difference in former 1/3 chord of blade tip has decreased clearly which benefits to reduce the strength of leakage flow in tip region. Therefore, the flow deterioration in tip region of transonic rotor induced by root fillet has been well suppressed, with an obvious improvement of overall performance occurring in new rotors.

Cite this article

CUI Weiwei, LIU Yuqiang, LIU Fusong, RUAN Changlong, YANG Laishun, LI Longting, YAO Fei, WANG Xinglu, WANG Cuiping . Effect of Geometric Variation of Root Fillet on the Flow Characteristic of a Transonic Compressor Rotor[J]. Journal of Thermal Science, 2023 , 32(4) : 1407 -1420 . DOI: 10.1007/s11630-023-1815-x

References

[1] Zeinalzadeh A., Pakatchian M.R., Evaluation of novel-objective functions in the design optimization of a transonic rotor by using deep learning. Engineering Applications of Computational Fluid Mechanics, 2021, 15(1): 561–583. 
[2] Deburge L.L., The aerodynamic significance of fillet geometry in turbocompressor blade rows. Journal of Engineering for Gas Turbines and Power, 1980, 102(4): 984–993. 
[3] Li J.B., Li X., Ji L.C., Yi W.L., Zhou L., Use of blended blade and end wall method in compressor cascades: Definition and mechanism comparisons. Aerospace Science and Technology, 2019, 92: 738–749. 
[4] Hoeger M., Baier R.D., Muller R., Engber M., Impact of a fillet on diffusing vane end-wall flow structure. Proceedings of the 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, Honolulu, Hawaii, USA, 2006, ISROMAC-11.
[5] Hoeger M., Schmidt-Eisenlohr U., Gomez S., Sauer H., Müller R., Numerical simulation of the influence of a bulb and a fillet on the secondary flow in a compressor cascade. TASK Quarterly, 2019, 6(1): 25–37.
[6] Li L.P., Chu W.L., Zhang H.G., Mechanism study of end-wall fillet’s influence on performance and flow field of high-load compressor cascade. Journal of Propulsion Technology, 2017, 38(12): 2743–2752. 
[7] Reutter O., Hemmert-Pottmann S., Hergt A., Nicke E., End-wall contouring and fillet design for reducing losses and homogenizing the outflow of a compressor cascade. Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, Düsseldorf, Germany, 2014, 6: 16–20. DOI: 10.1115/GT2014-25277.
[8] Kügeler E., Nürnberger D., Weber A., Engel K., Influence of blade fillets on the performance of a 15-stage gas turbine compressor. Proceedings of ASME Turbo Expo 2008: Power for Land, Sea and Air, Berlin, Germany, 2008, 6: 9–13. DOI: 10.1115/GT2008-50748.
[9] Curlett B.P., The aerodynamic effect of fillet radius in a low-speed compressor cascade. Washington, DC: National Aeronautics and Space Administration, 1991.
[10] Meyer R., Schulz S., Liesner K., A parameter study on the influence of fillets on the compressor cascade performance. Journal of Theoretical and Applied Mechanics, 2012, 50(1): 131–145.
[11] Kienzle N., Hoang D., Waesker M., Buelten B., Mare F., Doetsch C., Influence of fillet radii on the flow and strength behavior of a shrouded centrifugal compressor impeller. Proceedings of 14th European Conference on Turbomachinery Fluid dynamics & Thermodynamics, Gdansk, Poland, 2021, 4: 12–16. DOI: 10.29008/ETC2021-638.
[12] Tweedt D., Okiishi T., Stator blade row geometry modification influence on two-stage. Axial-Flow Compressor Aerodynamic Performance, 1983. DOI: 10.21236/ada141793.
[13] Goodhand M.N., Miller R.J., The impact of real geometries on three-dimensional separations in compressors. Journal of Turbomachinery, 2012, 134(2): 021007. 
[14] Justin J.O., The effects of blade fillets on aerodynamic performance of a high-pressure ratio centrifugal compressor. The 23rd International Compressor Engineering Conference, Purdue University, USA, 2016, 7: 11–14. 2016-1048, 
https://docs.lib.purdue.edu/icec/2396.
[15] Liu H.Q., Chi Z.R., Zhang J.X., Influence of root fillet on the structural and aerodynamic performance of a centrifugal impeller. IGTC Congress Proceedings, Tokyo, Japan, 2015, IGTC2015-51.
[16] Gao L.M., Cai Y.T., Li P., Li R.Y., Influence of blade-root fillet on transonic rotor performance. Journal of Mechanical Engineering, 2016, 52(20): 137–143. 
[17] Strazisar A.J., Wood J.R., Hathaway M.D., Laser anemometer measurements in a transonic axial-flow fan rotor. NASA: Cleveland, OH, USA, 1989.
[18] Naseri A., Boroomand M., Sammak S., Numerical investigation of effect of inlet swirl and total pressure distortion on performance and stability of an axial transonic compressor. Journal of Thermal Science, 2016, 25(6): 501–510.
[19] Kim S., Pullan G., Hall C.A., Stall inception in low pressure ratio fans. Journal of Turbomachinery, 2019, 141(7): 071005. 
[20] Niazi S., Numerical simulation of rotating stall and surge alleviation in axial compressor. Georgia Institute of Technology, Georgia, America, 2000.
[21] Hah C., Wennerstrom A.J., Three-dimensional flow fields inside a transonic compressor with swept blades. Journal of Turbomachinery, 1991, 113(2): 241–250. 
[22] Cai Y.J., Zhong Y.L., Qian L.H., He S.Z., Pang Q.H., Increasing surge margin in an axial flow compressor using “end-bend” airfoils. International Gas Turbine Symposium and Exposition, Beijing, China, 1985, 9: 1–7. DOI: 10.1115/85-IGT-25.
[23] Li Z.H., Liu Y.M., Blade-end treatment for axial compressors based on optimization method. Energy, 2017, 126(1): 217–230. 
[24] Wang Z.Q., Han W.J., Xu W.Y., The Effect of blade curving on flow characteristics in rectangular turbine stator cascades with different incidences. International Gas Turbine and Aeroengine Congress and Exposition, Orlando, Florida, USA, 1991, 6: 3–6. 
DOI: 10.1115/91-GT-060.
[25] Weingold H.D., Neubert R.J., Behlke R.F., Potter G.E., Reduction of compressor stator end-wall losses through the use of bowed stators. International Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas, USA, 1995, 6: 5–8. DOI: 10.1115/95-GT-380.
[26] Robinson C.J., Northall J.D., McFarlane C.W.R., Measurement and calculation of the three-dimensional flow in axial compressor stators, with and without End-Bends. ASME International Gas Turbine and Aeroengine Congress and Exposition, Toronto, Canada, 1989, 6: 4–8. DOI: 10.1115/89-GT-6.
[27] Wang Z.Q., Zheng Y., Research status and development of the bowed-twisted blade for turbomachines. Engineering Science, 2000, 2(6): 40–48.
[28] Sasaki T., Breugelmans F.E., Comparison of sweep and dihedral effects on compressor cascade performance. Journal of Turbomachinery, 1998, 120(2): 454–464. 
[29] Song Y.P., Li N., Wang S.T., Wang Z.Q., Effects of curved rotor on the performance of axial flow transonic compressor. Journal of Engineering Thermophysics, 2004, 25(4): 582–584.
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