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Study of Noise Reduction Based on Optimal Fan Outer Pressure Ratio and Thermodynamic Performance for Turbofan Engines at Conceptual Design Stage

  • Rui XueEmail author
  • Jun Jiang
  • Xing Zheng
  • Jian-liang Gong
  • Anthony Jackson
Original Paper
  • 24 Downloads

Abstract

With the development of civil aero-engines, the noise emission is now an essential issue to be considered during engine design. In this study, the preliminary design for a model fan, which was used for the fan noise estimation, was carried out. The fans with different bypass ratios, different tip speed as well as different aspect ratio were designed and the rough dimensions of the fan were obtained. Based on the dimension and performance of the fan, the effect of fan bypass ratio, tip speed, rotor blade numbers, and rotor–stator spacing on noise generation was investigated. The results indicate that the fan noise can be reduced as high as 10 dB by the increase of bypass ratios, and fewer rotor blade numbers and larger rotor–stator spacing are proved to be benefit to the fan noise reduction as well. However, lower tip speed does not achieve the noise reduction as expected. This is because more rotor blades are added to maintain the constant fan pressure ratio for the fan with lower tip speed. The study demonstrates that trade-off study should be carried out when considering fan noise reduction during engine design.

Keywords

Gas turbine Fan design Fan noise reduction 

Abbreviations

BPF

Blade passage frequency

BPR

Bypass ratio

EPNdB

Effective perceived noise decibel

FOPR

Fan outer pressure ratio

IGV

Inlet guide vane

ISA

International standard atmosphere

OASPL

Overall sound pressure level

OGV

Outlet guide vane

OPR

Overall pressure ratio

PNdB/PNDB

Perceived noise scales

PR

Pressure ratio

QAT

Quiet aircraft technology

RPM

Revolutions per minute

SLS

Sea level static

SPL

Sound pressure level

Dtip

Tip diameter

Dhub

Hub diameter

Notes

Funding

This work has been supported by the National Natural Science Foundation of China (51706170), China Postdoctoral Science Special Foundation (2019TQ0246), the Foundation of State Key Laboratory of Coal Combustion (FSKLCCA2004), the Fundamental Research Funds for the Central Universities, SCUT (xzy012019053), and China Postdoctoral Science Foundation (2019M663734).

Compliance with ethical standards

Conflict of interest

The authors declare that there is no conflict of interest.

References

  1. 1.
    Rolls-Royce plc (2015) The jet engine. Wiley-Blackwell, ChichesterGoogle Scholar
  2. 2.
    Sarvesh S (2010) Aero acoustics of high bypass fans. Department of Aerospace Engineering, Indian Institute of Technology, BombayGoogle Scholar
  3. 3.
    Kobayashi H, Koh M, Ozaki S, Yokichi M, Sato T (2006) Newly-developed adaptive noise absorption control technology for high speed fan noise reduction. JSME Int J 49:703–712CrossRefGoogle Scholar
  4. 4.
    Dennis L (2007) Huff, noise reduction technologies for turbofan engines. Glenn Research Center, ClevelandGoogle Scholar
  5. 5.
    Envia E (2001) Fan noise reduction: an overview/edmane envia. AIAA, RestonGoogle Scholar
  6. 6.
    Naumann R (1992) Control of the wake from a simulated blade by trailing edge blowing. Master’s Thesis, Lehigh University, BethlehemGoogle Scholar
  7. 7.
    Sell J (1997) Cascading testing to assess the effectiveness of mass addition/removal wake management strategies for reduction of rotor-stator interaction noise. Master’s Thesis, M-IT, CambridgeGoogle Scholar
  8. 8.
    Waitz IA, Brookfield JM, Sell J, Hayden B (1996) Preliminary assessment of wake management strategies for reduction of turbomachinery fan noise. AIAA J Propul Power 12(5):958–966CrossRefGoogle Scholar
  9. 9.
    Brookfield JM (1998) Turbofan rotor/stator interaction noise reduction through trailing edge blowing. Ph.D. Thesis, MIT, CambridgeGoogle Scholar
  10. 10.
    Fite EB, Woodward RP, Podboy GG (2006) Effect of trailing edge flow injection on fan noise and aerodynamic performance, AIAA-2006-2844Google Scholar
  11. 11.
    Kraft RE, Janardan BA, Kontos GC, Gliebe PR (1994) Active control of fan noise-feasibility study, volume 1: flyover system noise studies, NASA/CR 195392Google Scholar
  12. 12.
    Heidelberg LJ, Hall DG, Bridges JE, Nallasamy M (1996) A unique ducted fan test bed for active noise control and aeroacoustics research. NASA/TM 107213 and AIAA Paper 96-I740Google Scholar
  13. 13.
    Envia E, Nallasamy M (1998) Design selection and analysis of a swept and leaned stator concept. J Sound Vib 228(4):793–836CrossRefGoogle Scholar
  14. 14.
    Rao GVR (1972) Use of leaning vanes for fan noise reduction. AIAA Paper 72-126Google Scholar
  15. 15.
    Woodward RP, Elliott DM, Hughes CE et al (1998) Benefits of swept-and-leaned stators for fan noise reduction. J Aircr 38(6):1130–1138CrossRefGoogle Scholar
  16. 16.
    Hughes CE, Podboy GG, Woodward RP et al (2005) The effect of bypass nozzle exit area on fan aerodynamic performance and noise in a modelturbofan simulator, ASME Turbo Expo 2005: power for land, sea, and air. Am Soc Mech Eng 2005:1241–1264Google Scholar
  17. 17.
    Walsh PP, Fletcher P (2008) Gas turbine performance, 2nd edn. Oxford Blackwell Science Ltd, OxfordGoogle Scholar
  18. 18.
    Ramsden KW, Zachos P (2013) Turbomachinery course notes-compressors. Unpublished course notes. Cranfield University, CranfieldGoogle Scholar
  19. 19.
    Saravanamuttoo HIH (2008) Gas turbine theory, 6th edn. Pearson Prentice Hall, Upper Saddle RiverGoogle Scholar
  20. 20.
    Smith MJT (1989) Aircraft noise. Cambridge University Press, CambridgeCrossRefGoogle Scholar
  21. 21.
    European Aviation Safety Agency (2013) EASA TYPE CERTIFICATE DATA SHEET: Rolls-Royce plc Trent XWB series engines, TCDS E.111, Issue 01, 07 February 2013Google Scholar
  22. 22.
    Xue R, Jiang J, Jackson A (2019) Effect of bypass ratio on optimal fan outer pressure ratio and performance for turbofan engines. Int J Aeronaut Sp Sci.  https://doi.org/10.1007/s42405-018-0134-z CrossRefGoogle Scholar
  23. 23.
    Miller C (1988) Euler analysis of a swirl recovery vane design for use with an advanced single-rotation propfan. Government Printing Office, Washington DC, U.SCrossRefGoogle Scholar
  24. 24.
    Jackson AJB (2009) Optimization of aero and industrial gas turbine design for the environment. PhD Thesis, School Of Engineering, Cranfield UniversityGoogle Scholar
  25. 25.
    Heidmann MF (1975) Interim prediction for fan and compressor source noise. NASA TM X-71763Google Scholar
  26. 26.
    Di Fiore dos Santos G (2006) A methodology for noise prediction of turbofan engines. PhD Thesis, Aeronautics Institute of Technology, ITA, São José dos CamposGoogle Scholar

Copyright information

© The Korean Society for Aeronautical & Space Sciences 2019

Authors and Affiliations

  1. 1.State Key Laboratory for Strength and Vibration of Mechanical Structures, Shaanxi Engineering Laboratory for Vibration Control of Aerospace Structures, School of AerospaceXi’an Jiaotong UniversityXi’anPeople’s Republic of China
  2. 2.AECC Xi’an Aero-Engine Control CompanyXi’anPeople’s Republic of China
  3. 3.Xi’an Modern Chemistry Research InstituteXi’anPeople’s Republic of China
  4. 4.Centre for Propulsion EngineeringCranfield UniversityBedfordshireUK

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