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Aerodynamic characteristic comparison of ultra-highly and normally loaded fans

Published online by Cambridge University Press:  22 October 2021

H. Cao Open the ORCID record for H. Cao [Opens in a new window] ,
Z.G Zhou Open the ORCID record for Z.G Zhou [Opens in a new window]  and
X.L. Ye Open the ORCID record for X.L. Ye [Opens in a new window]
H. Cao
Affiliation:
College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjingChina
Z.G Zhou*
Affiliation:
College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjingChina
X.L. Ye
Affiliation:
College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjingChina
*
[email protected]
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Abstract

To reduce fan noise and weight, according to the structural characteristics of a turbofan engine, a fan rotor with an ultra-low rotating speed is designed in this study by using a new concept of diffusion blade profiles in which the rotating speed of an ultra-highly loaded rotor is only 0.58 times that of a normally loaded rotor. To further examine the applicability of this rotor, its matching stator is also designed. The flow fields in the ultra-highly and normally loaded fan stages are simulated using the same numerical method to conduct an aerodynamic characteristic comparison. Compared with the normally loaded rotor, the sizes of the boundary layers on the blade surfaces, the wakes behind the blades and the flow losses of the ultra-highly loaded rotor are smaller. At the design point, the efficiency of the ultra-highly loaded fan stages is higher than that of the normally loaded stage; moreover, the surge margin of the former is evidently larger than that of the latter. The ultra-highly loaded fan could be a good candidate for use in Ultra-High Bypass Ratio Geared Turbofan (UHBRGT) technology.

Keywords

Load coefficientHigh bypass ratioGeared turbofanAerodynamic designFlow field simulation
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1293 , November 2021 , pp. 2021 - 2038
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

Dewanji, D., Rao, G.A. and van Buijtenen, J. Feasibility study of some novel concepts for high bypass ratio turbofan engines, Proc. ASME Turbo Expo, 2009, 1, pp 51–61, doi: 10.1115/GT2009-59166.Google Scholar
Kurzke, J. Fundamental differences between conventional and geared turbofans, Proc. ASME Turbo Expo, 2009, 1, pp 145–153, doi: 10.1115/GT2009-59745.Google Scholar
Kestner, B.K., Schutte, J.S., Gladin, J.C. and Mavris, D.N. Ultra high bypass ratio engine sizing and cycle selection study for a subsonic commercial aircraft in the N+2 timeframe, Proc. ASME Turbo Expo, 2011, 1, pp 127–137, doi: 10.1115/GT2011-45370.Google Scholar
Huff, D.L. NASA Glenn’s contributions to aircraft engine noise research, J. Aerosp. Eng., 2013, 26, (2), pp 218–250, doi: 10.1061/(ASCE)AS.1943-5525.0000283.CrossRefGoogle Scholar
Riegler, C. and Bichlmaier, C. The geared turbofan technologyopportunities, challenges and readiness status, 1st CEAS European Air and Space Conference, Berlin, Germany, 2007.Google Scholar
Maozhang, C and Jiebao, L. Fan/Compressor aero design technology for high bypass ratio turbofan, Acta Aeronaut. Astronaut Sin., 2008, 29, (3), pp 513–526.(in Chinese)Google Scholar
Envia, E. Fan noise reduction: an overview, Int. J. Aeroacoust., 2002, 1, (1), pp 43–64, doi: 10.1260/1475472021502668.CrossRefGoogle Scholar
Hall, C.A. and Crichton, D. Engine design studies for a silent aircraft, J. Turbomach., 2007, 129, (3), pp 479–487, doi: 10.1115/1.2472398.CrossRefGoogle Scholar
Burak, K., Eberhard, N. and Christian, V. Design of a highly efficient low-noise fan for ultra-high bypass engines, Proc. ASME Turbo Expo, 2006, 6, pp 185–194, doi: 10.1115/GT2006-90363.Google Scholar
Bewick, C.L., Adams, M.J. and Schwaller, P.J.G. Noise and aerodynamic design and test of a low tip speed fan, 7th AIAA/CEAS Aeroacoustics Conference and Exhibit, 2001, doi: 10.2514/6.2001-2268.CrossRefGoogle Scholar
Dickens, T. and Day, I. The design of highly loaded axial compressors, Proc. ASME Turbo Expo, 2009, 7, pp 57–67, doi: 10.1115/GT2009-59291.CrossRefGoogle Scholar
Merchant, A., Kerrebrock, J.L., Adamczyk, J.J. and Braunscheidel, E. Experimental investigation of a high pressure ratio aspirated fan stage, J. Turbomach., 2005, 127, (1), pp 43–51, doi: 10.1115/1.1812323.CrossRefGoogle Scholar
Schuler, B.J., Kerrebrock, J.K. and Merchant, A. Experimental investigation of a transonic aspirated compressor, J. Turbomach., 2005, 127, (2), pp 340–348, doi: 10.1115/1.1860575.Google Scholar
Xizhen, S., Sheng, Z. and Qiushi, L. Way of improving aerodynamic load coefficient of transonic axial fan rotor, Acta Aeronaut. Astronaut. Sin., 2009, 30, (1), pp 12–20.(in Chinese)Google Scholar
Svorcan, J., Stupar, S., Trivkovic, S. et al. Active boundary layer control in linear cascades using CFD and artificial neural networks, Aerosp. Sci. Technol., 2014, 39, pp 243–249, doi: 10.1016/j.ast.2014.09.010.CrossRefGoogle Scholar
Zhenggui, Z., Jinhuan, Z. and Cui, C. Aerodynamic Design of an Ultra-high Load and Ultra-low Rotating Speed Fan of High Bypass Ratio, Patent in China, 201510450214.3.(in Chinese)Google Scholar
Jinhuan, Z., Zhenggui, Z., Wenqiang, W. and Yuzhen, D. Aerodynamic design of an ultra-low rotating speed geared fan, Aerosp. Sci. Technol., 2017, 63, pp 73–81, doi: 10.1115/1.2472398.Google Scholar
Strazisar, A.J. and Powell, J.A. Laser anemometer measurements in a transonic axial-flow fan rotor, J. Eng. Gas Turbines Power, 1981, 103, (2), pp 430–437, doi: 10.1115/1.3230738.CrossRefGoogle Scholar
Denton, J.D. and Xu, L. The effects of lean and sweep on transonic fan performance, Proc. ASME Turbo Expo, 2002, 5, pp 23–32. doi: 10.1115/GT2002-30327.Google Scholar
Passrucker, H., Engber, M., Kablitz, S. and Hennecke, D.K. Effect of forward sweep in a transonic compressor rotor, Proc. Inst. Mech. Eng. Part A J. Power Energy, 2003, 217, (4), pp 357–365, doi: 10.1243/095765003322315414.CrossRefGoogle Scholar