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


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.


Gas turbine Fan design Fan noise reduction 



Blade passage frequency


Bypass ratio


Effective perceived noise decibel


Fan outer pressure ratio


Inlet guide vane


International standard atmosphere


Overall sound pressure level


Outlet guide vane


Overall pressure ratio


Perceived noise scales


Pressure ratio


Quiet aircraft technology


Revolutions per minute


Sea level static


Sound pressure level


Tip diameter


Hub diameter



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.


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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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