考虑变截面影响的航空发动机短舱声学模型及数值结果

ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2006, Vol. 27 ›› Issue (6): 1073-1079.

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A New Approach for the Acoustic Design of Aeroengine Nacelle with the Effect of Varying Cross-section Aera

WANG Xiao-yu, DU Lin, SUN Xiao-feng

Fluid and Acoustic Engineering Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 10083, China

Received:2005-06-07 Revised:2005-09-12 Online:2006-12-25 Published:2006-12-25

Abstract

Abstract: This paper presents a transfer element method (TEM), which can be used to predict the sound propagation in a varying cross-section duct with acoustic liners. Compared with the existing work, such as Mode-Matching method and Boundary Integral method, this method does not need the eigenvalue calculation arising from a lined duct and at the sometime it has a capability of treating varying flow Mach number. Various numerical simulations show that the present results agree with the existing data very well at the same geometrical condition. Finally, this method is extended to calculate the sound propagation in a finite length duct, which also shows very interesting results.

Key words: direct boundary element method, transfer element method, aircraft engine nacelle, varying area duct, liner

CLC Number:

O422

WANG Xiao-yu;DU Lin;SUN Xiao-feng. A New Approach for the Acoustic Design of Aeroengine Nacelle with the Effect of Varying Cross-section Aera[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2006, 27(6): 1073-1079.

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A New Approach for the Acoustic Design of Aeroengine Nacelle with the Effect of Varying Cross-section Aera

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