Optimization of the Active Control of Turboprop Cabin Noise

In this paper, a modified cost function is proposed in order to achieve the maximum noise attenuation using a set of secondary sources for a harmonically excited sound field. The modified cost function drives the error signal to the optimally attenuated sound field instead of minimizing the squared...

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Bibliographic Details
Published in:Journal of aircraft 2015-09, Vol.52 (5), p.1386-1393
Main Authors: Romeu, Jordi, Palacios, J. Ignacio, Balastegui, Andreu, Pamies, Teresa
Format: Article
Language:English
Subjects:
Acoustic properties
Acoustics
Active control
Acústica
Aerodynamics
Aeronaus
Aircraft
Aircraft cabin
Aircraft compartments
Attenuation
Cabins
Control
Control theory
Control-systems
Cost function
Efficiency
Energy
Enginyeria mecànica
Error
Error signals
Fields
Finite element method
Física
Laboratories
Mathematical analysis
Mathematical models
Mechanical engineering
Microphones
Narrowband
Noise
Noise control
Noise levels
Optimization
Placement
Propietats acústiques
Reduction
Sensors
Soroll
Sound fields
Sound-transmission
Turbomachines
Turbomàquines
Turboprops
Àrees temàtiques de la UPC
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Summary:In this paper, a modified cost function is proposed in order to achieve the maximum noise attenuation using a set of secondary sources for a harmonically excited sound field. The modified cost function drives the error signal to the optimally attenuated sound field instead of minimizing the squared pressure. Moreover, changing the value to which the error signals must be driven allows change of the control strategy from global to local. The modified cost function requires the knowledge of the attenuated sound field, which is a condition that is well suited to narrowband noises, as is the case of turboprops. A numerical example of the application of the cost function is carried out using a finite element model/boundary element model of a real turboprop, with the goal of minimizing the interior sound field in the cabin to about 17  m3. A maximum averaged attenuation of 7 dB at blade-passage frequencies is achieved using six secondary sources and six error sensors. Besides, when the same control system is tuned to achieve local control around the head of a seated crew member, 11 dB of attenuation is achieved.
ISSN:0021-8669
1533-3868
DOI:10.2514/1.C032431