The improvement of interior comfort is becoming an increasingly required target in the transport engineering field, with particular attention to the aviation one. Generally, an aircraft is affected by several noise sources, from the engine power unit to the broadband components, related to the turbulent boundary layer (TBL). In this contest, the leading industries, in cooperation with research centers and universities, are actually employed in the development of innovative passive/active solutions for the internal noise as well as vibrations control: such technological implications must, on the one hand, satisfy these design requirements as well as meet the current airworthiness regulations. The paper deals with the vibro-acoustic testing activity on a typical turboprop fuselage subjected to different external load conditions: the damping ratio and the transmission loss characterization has been performed for several materials, including two innovative viscoelastic treatments too. The results highlighted a very good behaviour of the novel viscoelastic foams in terms of both acoustic and thermal performance when compared to standard blanket supported by extra viscoelastic treatments offering a very interesting self-embedded solution with a good weight to performance ratio

D. Siano

M. Arena

M. Viscardi

Archivio della ricerca - Università degli studi di Napoli Federico II

 Italian Association of Aeronautics and Astronautics XXIV International Conference 18-22 September 2017 | Palermo – Enna, Italy   AN INNOVATIVE VISCOELASTIC TREATMENT FOR THE INTERNAL NOISE REDUCTION IN A                           REGIONAL AIRCRAFT  M. Viscardi1*, M. Arena1, D. Siano2  1Università degli Studi di Napoli “Federico II”, Industrial Engineering Department, Aerospace Section, Via Claudio, 21 – 80125 – Napoli, Italy  2Istituto Motori, CNR (National Research Council), Via Marconi 4 – 80125 – Napoli, Italy *massimo.viscardi@unina.it  ABSTRACT The improvement of interior comfort is becoming an increasingly required target in the transport engineering field, with particular attention to the aviation one. Generally, an aircraft is affected by several noise sources, from the engine power unit to the broadband components, related to the turbulent boundary layer (TBL). In this contest, the leading industries, in cooperation with research centers and universities, are actually employed in the development of innovative passive/active solutions for the internal noise as well as vibrations control: such technological implications must, on the one hand, satisfy these design requirements as well as meet the current airworthiness regulations. The paper deals with the vibro-acoustic testing activity on a typical turboprop fuselage subjected to different external load conditions: the damping ratio and the transmission loss characterization has been performed for several materials, including two innovative viscoelastic treatments too. The results highlighted a very good behaviour of the novel viscoelastic foams in terms of both acoustic and thermal performance when compared to standard blanket supported by extra viscoelastic treatments offering a very interesting self-embedded solution with a good weight to performance ratio.   Keywords: Damping, Finite Element Model, Noise Control, Viscoelasticity. 1 INTRODUCTION The foams whose damping properties are going to be discussed in this assessment can be labelled as viscoelastic materials. Viscoelasticity is a property of certain types of materials whose behaviour stands halfway between the viscous and the elastic ones, as the name suggests. The purpose of this assessment is to show the insulating properties of new viscoelastic foams designed specifically to have a high acoustic absorption coefficient and how they can be used effectively in aeronautical applications in order to enhance acoustic comfort by focusing on reaching high performances while always keeping an eye on lightweight materials [1-2]. Usually the sound damping materials used in aeronautical applications to insulate the cabin from external noise sources are the so-called blankets which consist of an assembly of two materials, one with viscoelastic properties that reduce the structure vibration by muffling the structure-borne noise transmission and one with a relatively high acoustic absorption coefficient – like fiberglass fabrics – that ensures a dampening of the airborne noise transmission. The viscoelastic foams that are going to be examined in this assessment offer the great advantage of combining both insulating properties An innovative viscoelastic treatment for the internal noise reduction                                       in a regional aircraft  Viscardi, Arena, Siano 2 into one material which is still lightweight, thus resulting easier to produce and highly efficient at the same time.  The foam used in the tests is made of polyurethane. The production process involves first the formation of the polyurethane polymer and then the injection of gas bubbles inside the polymer matrix, which creates cavities (or cells) throughout the whole material. Said injection must be carefully balanced since if the bubbles are injected too fast, the whole foam could collapse because the matrix is not stiff enough to hold the gas and if the bubbles are injected too slowly, chances are that the foam will not develop correctly. Specifically, the foams examined hereby are the 65-30 type and the 90-10 type whose properties are listed in Table 1. On the other hand, the blanket-like setup was obtained by assembling a viscoelastic foil directly fixed on the structure and foam-like polyester panels attached on one side of the foil. In such framework, each foam has been tested using a linear stiffened panel, expressly designed and manufactured, in order to simulate a portion of the fuselage shell [3].   Table 1: Examined materials properties. Data Foam 65-30 Foam 90-10 Viscoelastic sheet Polyester Blanket Elastic Modulus, E [MPa] 0.017 0.012 0.800 0.172 Poisson ratio, 𝜈 0.3 0.3 0.45 0.3 Density, ρ [Kg/m3] 65 90 1140 45  2 VIBRO-ACOUSTIC PERFORMANCE ASSESSMENT 2.1 Experimental modal set-up The structural test – as well as the acoustic test – was made on a panel with stringers to mock up the outer skin of a fuselage and the stiffening structure beneath. The panel was hung from a beam with two supports to simulate a free-free condition, Figure 1.     (a) Hammer test (b) Laser Scanning Vibrometry   Figure 1: Vibro-acoustic test set-up, Baseline configuration. An innovative viscoelastic treatment for the internal noise reduction                                       in a regional aircraft  Viscardi, Arena, Siano 3  A first test campaign was conducted to determine the dynamic performance, in particular the modal damping, of the panel both stand-alone and with the addition of materials: a hammer test was performed by measuring the accelerometric signal at a fixed point (roving hammer) and the acoustic signal recorded by a microphone, placed about 30 cm from the surface of the panel. A non-contact laser vibrometry investigation has allowed for reconstructing the Operational Deflection Shapes (ODS), considering in this case a constant force spectrum exerted by a piezo-electric actuator [4-6]. 2.2 Baseline configuration A FE (Finite Element) model of the test article has been realized adopting a 2D mesh: shell properties have been assigned both to the plate and to the stringers, Figure 2. The results achieved by normal modes analysis within MSC Nastran® environment are well-correlated with those experimentally evaluated, Figure 3, Table 2 [7-9].   Figure 2: Vibro-acoustic test set-up, Baseline configuration.         (a) Mode I (b) Mode II (c) Mode III  Figure 3: Vibro-acoustic test set-up, Baseline configuration.  Table 2: Modal frequencies correlation. Mode Test [Hz] FEM [Hz] Δ [Hz] Δ [%] I 168.31 167.03 1.27 0.76 II 207.35 202.98 4.37 2.10 III 227.06 236.04 8.98 3.80 IV 340.13 343.90 3.77 1.09 V 343.24 352.95 9.72 2.75  An innovative viscoelastic treatment for the internal noise reduction                                       in a regional aircraft  Viscardi, Arena, Siano 4 In “near-field” conditions, vibrational and acoustic transfer functions can be compared: the resonance responses peaks appear in fact in both spectral signals, Figure 4. The structural waves propagate as pressure waves too: in such a way, an index that defines the transformation of vibrational energy into acoustic disturbance, with the same external excitation. For undamped systems, such coupling behaviour is increasingly evident.    Figure 4: Vibro-acoustic response, Baseline configuration.  2.3 Materials damping effect The experimental modal analysis allows for estimating the damping ratio for each modal shape: the following Figure 5 shows the accelerometric transfer function for each of the above-mentioned materials. High modal damping levels up to 12% are achievable by the viscoelastic foam 65-30 as well as by the standard solution, made up of the blanket with the viscoelastic layer [10-11]. In these cases, the amplitude peaks at the resonant frequencies are much smaller than the baseline configuration, Figure 6.    (a) FRF – g/N (b) Modal damping  Figure 5: Frequency Response Functions and damping assessment.    An innovative viscoelastic treatment for the internal noise reduction                                       in a regional aircraft  Viscardi, Arena, Siano 5   (a) Foam 65-30 (b) Foam 90-10   (c) Viscoelastic sheet (d) Visco + Polyester  Figure 6: Vibro-acoustic responses, damping materials.  The Laser Doppler Vibrometer (LDV) Polytec 400®, was placed 1.5 m away from the panel [4]. The vibrating load was applied by means of a piezoelectric transducer, which excited the structure, following an appropriately amplified electrical signal. The output results of the LDV was the vibration velocity magnitude, averaged on all the single-point measurements, detected on a grid representative of panel surface. A set of ODS has been achieved within the spectral range [100 Hz; 1000 Hz], as shown in Figure 7. However, the parameter shown in the plots as a function of frequency, is the gain ratio output/input, which allows for the obtaining significant information about the vibration energy of the system and separate the magnitude from the external load that caused it. Generally, such dynamic parameter is measured as a ratio between two engineering units but in this case, the input piezo-electric force, has been evaluated by only its signal electrical voltage.                  An innovative viscoelastic treatment for the internal noise reduction                                       in a regional aircraft  Viscardi, Arena, Siano 6  Figure 7: Vibro-acoustic test set-up, Baseline configuration. 3 TRANSMISSION LOSS ASSESSMENT 3.1 Reverberating room: test set-up The acoustic test has been carried out in order to define the transmission loss (TL) level with reference to each structural configuration. Therefore, the test has been performed as follows: the sound source must be placed in an environment that ensures a reverberating acoustic field so that there is no influence from the direction of the measurement. Therefore, a loudspeaker has been placed to the bottom, inside a reverberating box, Figure 8.    (b) External microphone installation    (a) Experimental scheme  (c) PP Probe workstation  Figure 8: Vibro-acoustic test set-up, Baseline configuration.      An innovative viscoelastic treatment for the internal noise reduction                                       in a regional aircraft  Viscardi, Arena, Siano 7 3.2 Test results A white noise signal has been used as input for the loudspeaker, obtaining a pressure excitation on the panel measured by the two microphones. All these measurements are reduced at a fixed distance from the panel, very close to this one in order to avoid all the environment influence, and the average Sound Pressure Level (SPL) is estimated. TL measurements have been therefore performed: Figure 9 represents such results in great agreement with the mass law trend. Strictly speaking, the coupling of blanket and damping sheet seems to work better in the spectral range analysed. However, such conventional sidewall solution involves a mass increase much higher, up to 30%, compared to that obtainable thanks to an embedded viscoelastic foam as well as requiring additional installation costs.   Figure 9: Transmission Loss, ISO measurement.  4 CONCLUSIONS AND FURTHER DEVELOPMENTS  In recent years, it has considerably grown the market demand for increasingly performing and comfortable aircrafts as a new mandatory design target [12-15]. Usually the sound damping materials used in aeronautical applications to insulate the cabin from external noise sources are the so-called blankets which consist of an assembly of two materials, one with viscoelastic properties that reduce the structure vibration by muffling the structure-borne noise transmission and one with a relatively high acoustic absorption coefficient – like fiberglass fabrics – that ensures a dampening of the airborne noise transmission. The viscoelastic foams, examined in this assessment offer the great advantage of combining both insulating properties into one material which is still light-weight, thus resulting easier to produce and highly efficient at the same time. The weight added by such foams was a smaller fraction of the panel itself than the configuration including the viscoelastic layer with the standard polyester. These results were collected in a numerical database, and addressed to the further noise prediction on a full-scale fuselage model, by finite element analysis.   An innovative viscoelastic treatment for the internal noise reduction                                       in a regional aircraft  Viscardi, Arena, Siano 8 REFERENCES [1] M. Viscardi, M. Arena, D. Siano. Experimental and numerical assessment of innovative damping foams. International Journal of Mechanics, 10, pp. 329-335 (2016). [2] M. Viscardi, M. Arena, D. Siano. Design and testing of a prototype foam for lightweight technological applications. International Journal of Mechanics, 10, pp. 383-395 (2016).   [3] G. Vanore, A. Paonessa, G. Arena. Improved testing methods for structural damping evaluation in “Proceedings of AIDAA Congress”, Milan, Italy, (2009).  [4] C. R. Fuller, S. J. Elliot, P. A. Nelson. “Active Control of Vibration”. Academic Press, London, (1996).  [5] L. Beranek. “Noise Reduction”. Mc Graw-Hill, (1960).  [6] L. Beranek, I. L. Ver. “Noise and Vibration Control Engineering: Principles and Applications”. Whiley & Sons, New York, USA, (1992).  [7] M. Viscardi, M. Arena, G. Barra, L. Guadagno. Structural Performance Analysis of Smart Carbon Fiber Samples Supported by Experimental Investigation. International Journal of Mechanics, 10, pp. 376-382 (2016).  [8] M. Viscardi, M. Arena, G. Barra, L. Guadagno. Smart carbon-epoxy laminate with high dissipation properties for vibro-acoustic optimization in the turboprop aircraft. International Journal of Mechanics, 11, pp. 51-57 (2017).  [9] M. Di Giulio, G. Arena, A. Paonessa. Vibro-acoustic behaviour of composite fuselage structures using embedded viscoelastic damping treatments in “Proceedings of AIDAA Congress”, Milan, Italy, (2009).   [10] D. I. G. Jones. “Handbook of Viscoelastic Vibration Damping”. Whiley & Sons, New York, USA, (2001).  [11] R. Vaicaitis, M, Slazak. Design of Sidewall Treatment For Cabin Noise Control of a Twin Engine Turboprop Aircraft. NASA Contract Report 172245, Modern Analysis Inc., Ridgewood, New Jersey, December, (1983).  [12] A. Carbone, A. Paonessa, L. Lecce, F. Marulo. Cabin noise reduction for a new development turboprop commuter aircraft. AGARD CP-366 on Aerodynamics and Acoustics of Propeller, Toronto, (1984).  [13] M. Arena, A. De Fenza, M. Di Giulio, A. Paonessa, F. Amoroso. Progress in studying passive and active devices for fuselage noise reduction for next generation turboprop. CEAS Aeronautical Journal, 8 (2), pp. 303-312 (2017). [14] G. Sen Gupta. “Low frequency cabin noise reduction based on the intrinsic structural tuning concept”. NASA CR-145262, (1978). [15] F. Marulo, L. Lecce, G. Buono, A. Carbone, M. Cianciaruso. Theoretical studies on frame applied dynamic absorbers to reduce cabin vibration and noise of turboprop aircraft. L’AEROTEC. MISSILI SPAZIO, 64 (4), pp. 230–231 (1985). 

AN INNOVATIVE VISCOELASTIC TREATMENT FOR THE INTERNAL NOISE REDUCTION IN A REGIONAL AIRCRAFT

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Archivio della ricerca - Università degli studi di Napoli Federico II