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Research Papers

Flow-Induced Noise and Vibration in Aircraft Cylindrical Cabins: Closed-Form Analytical Model Validation

[+] Author and Article Information
Joana da Rocha1

Department of Mechanical Engineering, University of Victoria, Victoria, BC, V8W 2Y2, Canadajdarocha@uvic.ca

Afzal Suleman

Department of Mechanical Engineering, University of Victoria, Victoria, BC, V8W 2Y2, Canada

Fernando Lau

Departamento de Engenharia Mecânica (Aeroespacial), Instituto Superior Técnico, 1049-001 Lisboa, Portugal

1

Corresponding author.

J. Vib. Acoust 133(5), 051013 (Sep 20, 2011) (9 pages) doi:10.1115/1.4003935 History: Received April 21, 2010; Revised February 27, 2011; Published August 31, 2011; Online September 20, 2011

The turbulent boundary layer is a major source of interior noise in transport vehicles, mainly in aircraft during cruise flight. Furthermore, as new and quieter jet engines are being developed, the turbulent flow-induced noise will become an even more important topic for investigation. However, in order to design and develop systems to reduce the cabin interior noise, the understanding of the physical system dynamics is fundamental. In this context, the main objective of the current research is to develop closed-form analytical models for the prediction of turbulent boundary-layer-induced noise in the interior of aircraft cylindrical cabins. The mathematical model represents the structural-acoustic coupled system, consisted by the aircraft cabin section coupled with the fuselage structure. The aircraft cabin section is modeled as a cylindrical acoustic enclosure, filled with air. The fuselage structure, excited by external random excitation or by turbulent flow, is represented through two different models: (1) as a whole circular cylindrical shell with simply supported end caps and (2) as a set of individual simply supported open circular cylindrical shells. This paper presents the results obtained from the developed analytical framework and its validation through the successful comparison with several experimental studies. Analytical predictions are obtained for the shell structural vibration and sound pressure levels, for the frequency range up to 10,000 Hz.

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Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 2

Noise reduction for the validation case 1. (a) From our analytical framework. (b) From Ref. 13: (—) predictions; (- - -) measurements.

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Figure 3

SPL for the validation case 2. (a) From our analytical framework. (b) From Ref. 34: (—) with attached floor; (- - -) without attached floor.

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Figure 1

Schematics of (a) closed circular cylindrical shell and (b) open shell

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Figure 4

Shell vibration level. From our analytical framework: (a) at (x,θ)=(0.5a,0.5θ0), (b) at (x,y)=(0.33a,0.5θ0), and (c) average values; (⋯) random excitation; (—) TBL excitation. From (12): (d).

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Figure 5

Sound pressure levels. From our analytical framework: (a) at (x,θ,r)=(0.3Lx,0.5θ0,0.5R), (b) at (x,θ,r)=(0.3Lx,0.5θ0,0), and (c) average values; (⋯) one shell excited by random noise; (thin line (—)) one shell excited by the TBL; (thick line (—)) 12 shells excited by the TBL. From (12): (d).

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