Relevant bibliographies by topics / Turbofan intake noise radiation

Academic literature on the topic 'Turbofan intake noise radiation'

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Published: 8 June 2024

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Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Conference papers

Journal articles on the topic "Turbofan intake noise radiation":

1

Palma, Giorgio, Lorenzo Burghignoli, Francesco Centracchio, and Umberto Iemma. "Innovative Acoustic Treatments of Nacelle Intakes Based on Optimised Metamaterials." Aerospace 8, no. 10 (October 14, 2021): 296. http://dx.doi.org/10.3390/aerospace8100296.

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Modern turbofans with high bypass ratios, low blade passage frequencies and short nacelles require continuous development of acoustic linings to achieve the noise reductions expected by the international aviation authorities. Metamaterials and metafluids have been recently proposed as promising technologies for designing innovative acoustic treatments dedicated to reducing aeronautic turbofan noise emissions. In this work, a phase-gradient metasurface treatment is investigated as a way to tackle the noise radiation from an axially symmetric nacelle. This paper aims to study the potential benefits of the mentioned technology, and is not an attempt to design a complete new liner or nacelle. The metasurface is modelled through an equivalent metafluid, and a simulation-based optimisation is used in defining the design parameters. The tonal contribution of the blade passage frequency is considered, and the numerical results with the metafluid optimised on one azimuthal mode at a time show a significant effect in terms of acoustic levels and directivity over an arc of virtual receivers.
2

Guérin, S., and A. Holewa. "Fan tonal noise from aircraft aeroengines with short intake: A study at approach." International Journal of Aeroacoustics 17, no. 6-8 (August 7, 2018): 600–623. http://dx.doi.org/10.1177/1475472x18789001.

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This work assesses the risks of increased fan noise for high bypass ratio aeroengines with short intakes. The close proximity between the fan and inlet contributes to the increase in radiation of the rotor-alone tones and reinforces the interaction of the inflow distortion with the fan. Thus, the closer the fan is to the inlet, the higher the risk for noise generation. This article discusses the results of Harmonic Balance simulations performed on a conceptual turbofan operated at the approach condition. The inflow distortion created by the nacelle incidence is dominated by the circumferential component [Formula: see text] = 1. Its presence is visible throughout the nacelle. A thorough analysis of the unsteady pressure and velocity fields shows that the new acoustic source created by the periodic unsteady loading of the rotor cutting the inflow distortion is negligible compared to the rotor–stator interaction. But the amplitude of the rotor–stator interaction tones is affected by the unsteadiness of the rotor wake shape, particularly in the tip region where a pronounced flow separation on the rotor blade is created at a certain range of azimuthal position. The variations of the flow incidence at the rotor leading edge, due to the axial and tangential components of the mean velocity, cannot explain that flow separation. Instead, the origin is attributed to the azimuthal variations of the radial component of the mean flow velocity near the casing which slightly points inward to the spinner, i.e. in the opposite direction of the casing contour line. The flow separation induces a pronounced scattering of the wake azimuthal components mw = hB into [Formula: see text] in the tip region, whereas the same effect is rather limited on the rest of the blade height. This leads to a moderate increase of the tonal sound power level compared to the case with clean inflow. The azimuthal scattering due to the propagation of the sound waves through the distortion is found to be weak in the bypass duct. However, this effect is very important in the inlet lip vicinity, where the strong asymmetry of the flow modifies the path of the sound waves up to the far field.
3

Groeneweg, J. F., and E. J. Rice. "Aircraft Turbofan Noise." Journal of Turbomachinery 109, no. 1 (January 1, 1987): 130–41. http://dx.doi.org/10.1115/1.3262058.

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Recent advances in the understanding of turbofan noise generation and suppression in aircraft engines are reviewed with particular emphasis on NASA research. The review addresses each link in the chain of physical processes which connect unsteady flow interactions with fan blades to far field noise. Mechanism identification and description, duct propagation, radiation, and acoustic suppression are discussed. Recent advances in the experimental technique of fan inflow control assure that inflight generation mechanisms are not masked by extraneous sources in static tests. Rotor blade surface pressure and wake velocity measurements aid the determination of the types and strengths of the generation mechanisms. Approaches to predicting or measuring acoustic mode content, optimizing treatment impedance to maximize attenuation, translating impedance into porous wall structure, and interpreting far field directivity patterns are illustrated by comparisons of analytical and experimental results. A persistent theme of the review is the interdependence of source and acoustic treatment design to minimize far field noise. Areas requiring further research are discussed and the relevance of aircraft turbofan results to quieting other turbomachinery installations is addressed.
4

Özyörük, Y., E. Alpman, V. Ahuja, and L. N. Long. "Frequency-domain prediction of turbofan noise radiation." Journal of Sound and Vibration 270, no. 4-5 (March 2004): 933–50. http://dx.doi.org/10.1016/s0022-460x(03)00640-0.

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5

Korotin, P. I., O. A. Potapov, G. E. Fiks, I. S. Fiks, Ia S. Pochkin, and I. D. Khaletskii. "Active noise suppression in the model of turbofan intake duct." Aviation Engines, no. 2 (2021): 7–16. http://dx.doi.org/10.54349/26586061_2021_2_7.

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6

Polacsek, C., and S. Burguburu. "Fan Interaction Noise Predictions Using RANS-BEM Coupling." International Journal of Aeroacoustics 4, no. 1-2 (January 2005): 153–67. http://dx.doi.org/10.1260/1475472053729987.

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A source-to-far-field computation procedure aiming at predicting the noise generated by rotor-stator fan interactions and inlet noise radiation is presented here. It is applied to the NLR turbofan model, tested in DNW-LLF anechoic chamber under the framework of DUCAT project. The unsteady aerodynamic input for the acoustic computation is obtained using a 3D RANS code, CANARI, developed at ONERA for turbomachinery applications. The CFD solutions are coupled, using a modal expansion approach, to a BEM code, solving the Helmholtz equation in an arbitrary bounded space. A single interacting cut-on mode amplitude is either directly deduced from experiment or provided by post-processing the CFD data. With this approach, the predicted noise radiation can be related to the directivity patterns measured at several axial positions upstream of the turbofan inlet. A fairly good agreement is found using both experimental and CFD input data.
7

Rouvas, D.-M., and A. McAlpine. "Prediction of Fan Tone Radiation Scattered By A Cylindrical Fuselage." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012050. http://dx.doi.org/10.1088/1757-899x/1226/1/012050.

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Abstract A theoretical prediction method of the scattering of fan tone radiation from a turbofan inlet duct by the airframe fuselage is presented. The fan tone noise is modelled by an acoustic disc source that represents the sound field at the inlet duct termination. Adjacent to the source is a cylindrical fuselage that scatters the fan tone radiation. The prediction method is valid for upstream sound radiation. The acoustic pressure on the cylindrical fuselage is affected by refraction of the sound as it propagates through the fuselage boundary layer. This effect known as boundary layer shielding is more prominent forward of the turbofan, since the fan tone noise radiated from the inlet duct is propagating upstream. An asymptotic approach is used to model sound propagation through a boundary layer which is modelled by a thin linear shear velocity profile. Consequently the scattered pressure field can be computed very quickly, thus providing a fast and efficient prediction method. Although a realistic fuselage turbulent boundary layer does not resemble a linear shear layer, it is shown that the effect of acoustic shielding by a turbulent boundary layer can be modelled by taking a liner shear profile with a shape factor that matches the shape factor for a realistic turbulent profile.
8

Parrett, A. V., and W. Eversman. "Wave envelope and finite element approximations for turbofan noise radiation in flight." AIAA Journal 24, no. 5 (May 1986): 753–60. http://dx.doi.org/10.2514/3.9342.

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9

Kholodov, Pavel, and Stéphane Moreau. "Identification of Noise Sources in a Realistic Turbofan Rotor Using Large Eddy Simulation." Acoustics 2, no. 3 (September 22, 2020): 691–706. http://dx.doi.org/10.3390/acoustics2030037.

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Large Eddy Simulation is performed using the NASA Source Diagnostic Test turbofan at approach conditions (62% of the design speed). The simulation is performed in a periodic domain containing one fan blade (rotor-alone configuration). The aerodynamic and acoustic results are compared with experimental data. The dilatation field and the dynamic mode decomposition (DMD) are employed to reveal the noise sources around the rotor. The trailing-edge radiation is effective starting from 50% of span. The strongest DMD modes come from the tip region. Two major noise contributors are shown, the first being the tip noise and the second being the trailing-edge noise. The Ffowcs Williams and Hawkings’ (FWH) analogy is used to compute the far-field noise from the solid surface of the blade. The analogy is computed for the full blade, for its tip region (outer 20% of span) and for lower 80% of span to see the contribution of the latter. The acoustics spectrum below 6 kHz is dominated by the tip part (tip noise), whereas the rest of the blade (trailing-edge noise) contributes more beyond that frequency.
10

Duta, M. C., and M. B. Giles. "A three-dimensional hybrid finite element/spectral analysis of noise radiation from turbofan inlets." Journal of Sound and Vibration 296, no. 3 (September 2006): 623–42. http://dx.doi.org/10.1016/j.jsv.2006.03.006.

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Journal articles

Dissertations / Theses on the topic "Turbofan intake noise radiation":

1

Ulusoy, Yavuz Barbaros. "Frequency Domain Computation Of Turbofan Exhaust Noise Radiation." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/12607234/index.pdf.

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In this study, acoustic noise radiation through a duct in frequency domain is analyzed. Frequency domain linearized Euler equations are solved for turbofan exhaust noise propagation and radiation. The geometry in studied cases is assumed as axisymmetric. The acoustic waves are decomposed into periodic azimuthal modes. Characteristic boundary conditions, and buffer zone boundary conditions are employed. Iterative type pseudo time integration is employed. Nonuniform background flow effect on the radiation pattern is experienced. All computations are performed in parallel using MPI library routines in computer cluster. Results proved that the one with the buffer zone has a better radiation characteristic than the characteristic one because of absorbtion of spurious waves. It is seen that the efficiency of the buffer zone is frequency dependent.
2

Kewin, Matthew Fergus. "Acoustic liner optimisation and noise propagation through turbofan engine intake ducts." Thesis, University of Southampton, 2013. https://eprints.soton.ac.uk/366367/.

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The research in this thesis explores the prediction of fan noise propagation through turbofan engine intakes and its radiation to the far-field. The performance of acoustic liners installed in intakes to attenuate noise is the focus of the study. A commercial CAA (Computational AeroAcoustics) code ACTRAN/TM and an in-house shell code ANPRORAD developed at the ISVR are used to predict the performance of acoustic liners throughout the studies presented in this thesis. An automated system for running computations for a large number of cases with different liner impedance and engine operating conditions has been developed and applied for optimising liners for maximum noise benefit. The intake liner configuration of main interest is an intake lip liner. The performance of liners are investigated for broadband and tone noise source components of fan noise. In the study for an intake lip liner, an optimum single layer was identified based on the optimisations. A series of no-flow scale rig tests were conducted in the anechoic chamber at the ISVR and the test data have been appraised by comparing with numerical predictions. Reasonable agreements have been achieved, and the lip liner showed measurable noise benefit. Numerical predictions of a lip liner performance have also been performed for a fan rig intake tested in the presence of flow.
3

Detwiler, Kevin P. "Reduced fan noise radiation from a supersonic inlet." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-09192009-040457/.

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4

de, la Riva Diego Horacio. "Modeling of Herschel/Quincke-Liner Systems for the Control of Aft Fan Radiation in Turbofan Engines." Diss., Virginia Tech, 2006. http://hdl.handle.net/10919/28080.

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Commercial aviation transportation has experienced an overwhelming growth over the years. However, this expansion has encountered an important barrier: noise. Several studies have shown that residents in these areas experience problems such as stress and sleep disturbance. These problems have translated into demands for a better quality of life from airport residents which in turn have translated into more stringent aircraft noise regulations. As a result, large amounts of resources have been diverted towards the improvement of existing noise attenuation technologies and the development of more effective ones. In terms of turbofan generated noise, the most widely used technology is that of absorbent materials or liners. In recent investigations Alonso et al. have combined Herschel/Quincke (HQ) tubes with liners. This combination has the potential of effectively controlling pure tones and broadband noise in inlet sections of modern turbofan engines. Since a comprehensive approach for engine noise reduction will involve both inlet and aft HQ-Liner systems, additional research efforts were needed to evaluate their performance at reducing aft fan radiation In the present work, a combination of traditional liners and Herschel/Quincke waveguide resonators for aft fan radiation control is proposed. A theoretical model is developed in order to predict noise reduction due to such systems. The newly developed tool was then utilized to design an HQ-liner that was installed and tested in the aft section of the NASA Active Noise Control Fan (ANCF) rig. This experimental data was utilized to prove the potential of these systems and to validate the mathematical model. Analytical predictions correlate well with experiments. The NASA ANCF rig is not representative of a real turbofan engine. In order to assess the behavior of HQ-Liners in a more realistic environment a new system was specifically designed for a generic turbofan engine and its performance analyzed. The sound field inside HQ tubes has been described assuming plane waves only. This assumption limits the model to frequencies below the tube first resonance. In order to overcome this limitation a new model accounting for higher order modes inside the tubes has been developed.
Ph. D.
5

Marchner, Philippe. "Non-reflecting boundary conditions and domain decomposition methods for industrial flow acoustics." Electronic Thesis or Diss., Université de Lorraine, 2022. http://www.theses.fr/2022LORR0094.

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Ce travail de thèse est consacré aux méthodes de décomposition de domaine de Schwarz sans recouvrement pour la résolution de problèmes industriels hautes fréquences d'acoustique en écoulement. Les méthodes de résolution en régime harmonique sont difficiles à paralléliser en raison de leur caractère oscillatoire, si bien que les méthodes actuelles sont limitées par une fréquence maximale, imposée par la mémoire disponible de l'ordinateur. Les méthodes de Schwarz sans recouvrement divisent le domaine en sous-domaines d'un point de vue continu et fournissent un cadre approprié en vue d'une parallélisation à mémoire distribuée. Le problème est résolu de manière itérative sur les inconnues d'interface, où la convergence rapide repose sur des conditions de transmission appropriées. La première partie de cette thèse est consacrée à la conception d'opérateurs de transmission adaptés à la propagation d'ondes harmoniques en milieu convecté et hétérogène. Dans ce cadre nous étudions deux catégories de conditions aux limites non-réfléchissantes qui fournissent des approximations locales de l'opérateur Dirichlet-to-Neumann. Dans un premier temps, des conditions aux limites absorbantes sont conçues basées sur l'analyse microlocale et le calcul pseudodifférentiel. Dans un second temps, la problématique de la stabilité acoustique en écoulement des couches parfaitement adaptées est abordée pour des domaines convexes par la transformation de Lorentz. La deuxième partie de cette thèse étend une méthode générique de décomposition de domaine à des problèmes d'acoustique en écoulement, et applique les conditions de transmission préalablement étudiées à des problèmes académiques simples. Nous expliquons le lien entre la méthode de Schwarz sans recouvrement et une factorisation algébrique LU par blocs du problème. Enfin, nous proposons une mise en œuvre parallèle et montrons l'intérêt de l'approche au rayonnement acoustique tridimensionnel de l'avant d'un turboréacteur d'avion
This PhD project is devoted to non-overlapping Schwarz domain decomposition methods for the resolution of high frequency flow acoustics problems of industrial relevance. Time-harmonic solvers are difficult to parallelize due to their high-oscillatory behaviour, and current solvers quickly reach an upper frequency limit dictated by the available computer memory. Non-overlapping Schwarz methods split the domain into subdomains at the continuous level and provide a suitable setting for distributed memory parallelization. The problem is solved iteratively on the interface unknowns, where the keystone for quick convergence relies on appropriate transmission conditions. The first part of this thesis is devoted to the design of transmission operators tailored to convected and heterogeneous time-harmonic wave propagation. To this end we study two non-reflecting boundary techniques that provide local approximations to the Dirichlet-to-Neumann operator. On the one hand, Absorbing Boundary Conditions are designed based on microlocal analysis and pseudodifferential calculus. On the other hand, the convected acoustic stability issue is addressed for Perfectly Matched Layers in convex domains with Lorentz transformation. The second part of this thesis describes how to adapt a generic domain decomposition framework to flow acoustics, and applies the newly designed transmission conditions to simple academic problems. We explain the relation between the non-overlapping Schwarz formulation and an algebraic block LU factorization of the problem. Finally we propose a parallel implementation of the method and show the benefit of the approach for the three-dimensional noise radiation of a high by-pass ratio turbofan engine intake
6

Mertens, Tanguy. "A new mapped infinite partition of unity method for convected acoustical radiation in infinite domains." Doctoral thesis, Universite Libre de Bruxelles, 2009. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210365.

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Résumé:

Cette dissertation s’intéresse aux méthodes numériques dans le domaine de l’acoustique. Les propriétés acoustiques d’un produit sont devenues une part intégrante de la conception. En effet, de nos jours le bruit est perçu comme une nuisance par le consommateur et constitue un critère de vente. Il y a de plus des normes à respecter. Les méthodes numériques permettent de prédire la propagation sonore et constitue dès lors un outil de conception incontournable pour réduire le temps et les coûts de développement d’un produit.

Cette dissertation considère la propagation d’ondes acoustiques dans le domaine fréquentiel en tenant compte de la présence d’un écoulement. Nous pouvons citer comme application industrielle, le rayonnement d’une nacelle de réacteur d’avion. Le but de la thèse est de proposer une nouvelle méthode et démontrer ses performances par rapport aux méthodes actuellement utilisées (i.e. la méthode des éléments finis).

L’originalité du travail consiste à étendre la méthode de partition de l’unité polynomiale dans le cadre de la propagation acoustique convectée, pour des domaines extérieurs. La simulation acoustique dans des domaines de dimensions infinies est réalisée dans ce travail à l’aide d’un couplage entre éléments finis et éléments infinis.

La dissertation présente la formulation de la méthode pour des applications axisymétriques et tridimensionnelles et vérifie la méthode en comparant les résultats numériques obtenus avec des solutions analytiques pour des applications académiques (i.e. propagation dans un conduit, rayonnement d’un multipole, bruit émis par la vibration d’un piston rigide, etc.). Les performances de la méthode sont ensuite analysées. Des courbes de convergences illustrent à une fréquence donnée, la précision de la méthode en fonction du nombre d’inconnues. Tandis que des courbes de performances présentent le temps de calcul nécessaire pour obtenir une solution d’une précision donnée en fonction de la fréquence d’excitation. Ces études de performances montrent l’intérêt de la méthode présentée.

Le rayonnement d’un réacteur d’avion a été abordé dans le but de vérifier la méthode sur une application de type industriel. Les résultats illustrent la propagation pour une nacelle axisymétrique en tenant compte de l’écoulement et la présence de matériau absorbant dans la nacelle et compare les résultats obtenus avec la méthode proposée et ceux obtenus avec la méthode des éléments finis.

Les performances de la méthode de la partition de l’unité dans le cadre de la propagation convectée en domaines infinis sont présentées pour des applications académiques et de type industriel. Le travail effectué illustre l’intérêt d’utiliser des fonctions polynomiales d’ordre élevé ainsi que les avantages à enrichir l’approximation localement afin d’améliorer la solution sans devoir créer un maillage plus fin.

Summary:

Environmental considerations are important in the design of many engineering systems and components. In particular, the environmental impact of noise is important over a very broad range of engineering applications and is increasingly perceived and regulated as an issue of occupational safety or health, or more simply as a public nuisance. The acoustic quality is then considered as a criterion in the product design process. Numerical prediction techniques allow to simulate vibro-acoustic responses. The use of such techniques reduces the development time and cost.

This dissertation focuses on acoustic convected radiation in outer domains such as it is the case for turbofan radiation. In the current thesis the mapped infinite partition of unity method is implemented within a coupled finite and infinite element model. This method allows to enrich the approximation with polynomial functions.

We present axisymmetric and three-dimensional formulations, verify and analyse the performance of the method. The verification compares computed results with the proposed method and analytical solutions for academic applications (i.e. duct propagation, multipole radiation, noise radiated by a vibrating rigid piston, etc.) .Performance analyses are performed with convergence curves plotting, for a given frequency, the accuracy of the computed solution with respect to the number of degrees of freedom or with performance curves, plotting the CPU time required to solve the application within a given accuracy, with respect to the excitation frequency. These performance analyses illustrate the interest of the mapped infinite partition of unity method.

We compute the radiation of an axisymmetric turbofan (convected radiation and acoustic treatments). The aim is to verify the method on an industrial application. We illustrate the radiation and compare the mapped infinite partition of unity results with finite element computations.

The dissertation presents the mapped partition of unity method as a computationally efficient method and illustrates its performances for academic as well as industrial applications. We suggest to use the method with high order polynomials and take the advantage of the method which allows to locally enrich the approximation. This last point improves the accuracy of the solution and prevent from creating a finer mesh.


Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished

Books on the topic "Turbofan intake noise radiation":

1

Center, NASA Glenn Research, ed. Turbofan noise propagation and radiation at high frequencies. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2003.

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2

Computation of noise radiation from turbofans: A parametric study. [Washington, D.C.?]: National Aeronautics and Space Administration, 1995.

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3

Computation of noise radiation from turbofans: A parametric study. [Washington, D.C.?]: National Aeronautics and Space Administration, 1995.

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4

Fan noise prediction system development: Source/radiation field coupling and workstation conversion for the acoustic radiation code. [Washington, DC: National Aeronautics and Space Administration, 1993.

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Conference papers on the topic "Turbofan intake noise radiation":

1

Zhang, Xinwen, Changchun Liu, and Bing Lin. "Prediction of Engine Intake Noise with Discontinuous Least-Square Finite Element Method in Frequency Domain Acoustics." In GPPS Xi'an21. GPPS, 2022. http://dx.doi.org/10.33737/gpps21-tc-195.

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In the frame of efficient passive treatment, intake noise prediction needs improving. This paper presents a novel numerical method for predicting acoustic propagation from axisymmetric ducted fans of high bypass ratio turbofan engine. Non-uniform mean flow convection and acoustic liner treatment is included. The linearized Euler equations are solved in the frequency domain. The spatial discretization is conducted with the discontinuous least-square finite element method so that the resulting algebraic equation is Hermitian conjugate symmetric. Moreover, the high-order accuracy and hp refinement is obtained while memory shared parallel computing strategy is used for convergence acceleration. Based on the near field acoustics, the porous Ffowcs Williams-Hawkings equation is solved for far field sound pressure level. Benchmark problems including monopole radiation in uniform mean flow and acoustic propagation in sheared mean flow are used to validate the capability. Simulations of the JT15D static test intake noise are performed, where the far field angle of peak sound pressure level, about 60° agrees well with experimental data and numerical data available in the literature.
2

Doherty, Martin, and Howoong Namgoong. "Impact of Turbofan Intake Distortion on Fan Noise Propagation and Generation." In 22nd AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-2841.

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Xiong, Lei, Rie Sugimoto, and Erika Quaranta. "Effects of turbofan engine intake droop and length on fan tone noise." In 25th AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-2581.

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4

Ait-Ali-Yahia, D., D. Stanescu, W. Habashi, and M. Robichaud. "Axisymmetric computations of fan noise radiation from turbofan inlets." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-483.

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Casalino, Damiano, and Mattia Barbarino. "Turbofan Aft Noise Radiation: Progress Towards a Realistic CAA Simulation." In 14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2882.

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Mincu, Daniel-Ciprian, Eric Manoha, Gabriel Reboul, Stephane Redonnet, and Sebastian Pascal. "Numerical simulation of broadband aft fan noise radiation for turbofan with scarfed nozzle." In 17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2941.

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Ozyoruk, Yusuf, and Stephane Lidoine. "Numerical Analysis of Noise Radiation from a Turbofan Exhaust Cowl with an Extended Liner in Flight." In 14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2880.

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Sugimoto, Rie, Alexander O. James, Alan McAlpine, and Richard J. Astley. "CFD/CAA coupling for the prediction of fan tone noise propagation and radiation through a drooped intake." In 28th AIAA/CEAS Aeroacoustics 2022 Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-3100.

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Rousselot, S., D. Truffi, G. Doulgeris, S. Mistry, V. Pachidis, and P. Pilidis. "Generation of a Quasi 3-D Map of a Half-Embedded Ultra High Bypass Ratio Turbofan Intake on the Wing of a Broad Delta Wing Airframe." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51008.

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The need for low fuel consumption, emissions and noise drives future propulsion systems towards ultra high bypass ratio turbofan configurations. One of the arising challenges is the installation of such an engine, due to its high diameter. An alternative to under-the-wing podded installation is half embedding it into a thick wing. An ideal airframe has been found to be the Broad Delta (BD) wing, featuring high wing-root thickness. Two conventional nacelles have been integrated into each wing of a four-engine BD body. The performance of a half embedded turbofan intake has been studied, with the use of 3-D Computational Fluid Dynamics. This qualitative analysis comprises of full scale aircraft simulation with special focus on the flow-field upstream and inside the novel installation. The study required the creation of a detailed map of the intake for cruise and take-off flight conditions. The map comprises of radial pressure recovery profiles in various circumferential positions for enhanced representation of fan-inlet total pressure distortion. It is produced using a decoupled zooming process, where ‘matching’ between a 0-D gas turbine performance code and 3-D CFD is achieved for each operating point.
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B., RajaGopal, Santosh Gannu, Abhilash M, GS Krishnamurthy, and Rod Giles. "Pass-by Noise Prediction of a Vehicle." In Small Engine Technology Conference & Exposition. 10-2 Gobancho, Chiyoda-ku, Tokyo, Japan: Society of Automotive Engineers of Japan, 2020. http://dx.doi.org/10.4271/2019-32-0593.

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<div class="section abstract"><div class="htmlview paragraph">The forthcoming pass-by noise regulations have impacted the automotive sector, which further leads to the reduction of noise in the vehicle. The prediction of pass-by noise at an early stage will reduce the overall cost as well as time for an automobile industry and helps to reduce the overall product development life cycle. This supports the design activities of a vehicle.</div><div class="htmlview paragraph">Msc ACTRAN/NASTRAN/ADAMS and GT Suite are major tools used in the present study to develop a simulation method to mimic the predefined testing norms. In Actran interior and exterior noise propagation is performed. Interior noise flow obtained by compressible flow analysis which uses exhaust/intake line velocity/temperature as boundary condition. The exterior noise propagation obtained by direct frequency response using acoustic duct mode with unit pressure injected into the intake and exhaust system and compressible flow field map results as input, this will take care of both noise propagation. Similarly for engine exterior noise radiation done by Nastran unit frequency response analysis and later actual loads from multi-body dynamics multiplied with direct frequency response analysis in Actran.</div><div class="htmlview paragraph">Finally the python script is developed to find the acoustic transfer function between the unit pressure pulse in Actran/Unit frequency response in Nastran, also the actual intake/exhaust pressure pulse excitation from 1D GT suite model/Actual engine Multibody loads that all are simultaneously multiply one by one for each engine revolution result gives the overall sound pressure levels radiated noise (OSPL) of the motorcycle.</div><div class="htmlview paragraph">It is observed that the final pass-by noise simulation results the main contributions of exhaust system are in acceptable range.</div></div>

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