Bibliografías temáticas / Numerical optimization and civil aircraft engine noise

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Literatura académica sobre el tema "Numerical optimization and civil aircraft engine noise"

Autor: Grafiati

Publicado: 9 de noviembre de 2024

Última modificación: 31 de julio de 2025

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Artículos de revistas sobre el tema "Numerical optimization and civil aircraft engine noise"

Chen, Min, Zihao Jia, Hailong Tang, Yi Xiao, Yonghang Yang, and Feijia Yin. "Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept." International Journal of Aerospace Engineering 2019 (January 14, 2019): 1–19. http://dx.doi.org/10.1155/2019/2918646.

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Supersonic civil aircraft is of a promising area in the development of future civil transport, and aircraft propulsion system is one of the key issues which determine the success of the aircraft. To get a good conceptual design and performance investigation of the supersonic civil aircraft engine, in this article, a fast, versatile as well as trust-worthy numerical simulation platform was established to analyze the Mach 4 turbine-based combined cycle (TBCC) engine concept so as to be applied to the supersonic civil aircraft. First, a quick and accurate task requirement analysis module was newl

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Zhou, Hangwei. "Fuselage panel structural-acoustic optimization design of civil aircraft based on numerical analysis." Journal of Physics: Conference Series 2882, no. 1 (2024): 012014. http://dx.doi.org/10.1088/1742-6596/2882/1/012014.

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Abstract During the design process of civil aircraft, it is necessary to achieve a high level of cabin noise control to improve cabin comfort. In addition to controlling the intensity of the main noise sources that affect the acoustic environment in the cabin, the acoustic optimization design of the fuselage wall panel structure is also required. In this paper, acoustic analysis software ACTRAN is applied to study the acoustic characteristics of typical structures of civil aircraft cabins. Boundary conditions, material density, and material damping are analyzed from the following main aspects:

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Moreau, Antoine, Andrej Prescher, Stephen Schade, Maikhanh Dang, Robert Jaron, and Sébastien Guérin. "A framework to simulate and to auralize the sound emitted by aircraft engines." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 1 (2023): 7160–71. http://dx.doi.org/10.3397/in_2023_1073.

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In civil aviation, the well-established Effective Perceived Noise Level (EPNL) has remained, so far, a simple but reliable psycho-acoustic metric, representing the backbone of noise regulation politics and leading to quieter aircraft turbofan engines. However, the recent changes induced by further acoustic optimization of engines, or the introduction of innovative designs, suggest that a more refined assessment than the sole EPNL metric is needed, which is based on sound auralization. The paper presents a framework of simulation tools that are currently being developed at the DLR Engine Acoust

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He, Sibo, Yimeng Li, Zidong Pu, and Wenbo Rao. "Aerodynamic Calculation and Computer Numerical Simulation Methods Applied in Jet Engine Research." Highlights in Science, Engineering and Technology 62 (July 27, 2023): 217–27. http://dx.doi.org/10.54097/hset.v62i.10446.

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The development status of aero-engines is a sign of a country's technological development level and comprehensive national strength. Jet engines undergone a rapid development since being invented and are widely applied in both commercial and military aircraft nowadays. The objective of jet engines is to provide thrust for aircraft and maintain high performance in different flight segments. Engine design choice must be compromised to balance different selection criteria. This article reviews the development history of jet engines and reviews the development paths of jet engines in various techn

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Ispir, Ali Can, Pedro Miguel Gonçalves, and Bayindir H. Saracoglu. "Analysis of a combined cycle propulsion system for STRATOFLY hypersonic vehicle over an extended trajectory." MATEC Web of Conferences 304 (2019): 03001. http://dx.doi.org/10.1051/matecconf/201930403001.

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Hypersonic civil aviation is an important enabler for extremely shorter flight durations for long-haul routes and using unexploited flight altitudes. Combined cycle engine concepts providing extended flight capabilities, i.e. propelling the aircraft from take-off to hypersonic speeds, are proposed to achieve high-speed civil air transportation. STRATOFLY project is a continuation of former European efforts in hypersonic research and aims at developing a commercial reusablevehicle for cruise speed of Mach 8 at stratospheric altitudes as high as 35 km above ground level. The propulsion plant of

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Li, Yejin, Peng Rao, Zhengda Li, and Jianliang Ai. "On-Board Parameter Optimization for Space-Based Infrared Air Vehicle Detection Based on ADS-B Data." Applied Sciences 13, no. 12 (2023): 6931. http://dx.doi.org/10.3390/app13126931.

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Frequent aviation safety accidents of civil aircraft misses and crashes lead to an urgent need for flight safety assurance. Due to long-time flights over different backgrounds, accompanied by the changes in flight altitude and speed, it is difficult for a conventional space-based infrared detection system to use a set of fixed parameters to meet the stable detection requirement. To enhance the awareness of civil aircraft surveillance, a real-time parameter optimization method based on Automatic Dependent Surveillance-Broadcast (ADS-B) data is proposed. According to the background spectral char

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Ghinet, Sebastian, Patrick Bouche, Thomas Padois, et al. "Overview of concept designs and results of the New Acoustic Insulation Meta-Material for Aerospace (NAIMMTA) project." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 5 (2023): 3402–13. http://dx.doi.org/10.3397/in_2023_0489.

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Reducing aircraft cabin noise to improve the comfort of passengers is an important and challenging issue in aeronautics. Relatively uncomfortable high noise levels of around 80 to 90 dBA with strong low frequency range components (below 500 Hz) and a tonal character, predominantly related to the engine fan during take-off and approach, are deemed critical. The conventional acoustic materials seem to have reached their physical limits in terms of sound proofing, and therefore non-conventional solutions, such as metamaterials, are sought for their promising performance such as, a significant noi

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LAFONT, Victor, Delphine SEBBANE, Frank SIMON, Jean-Paul PINACHO, and Julien CAILLET. "Feasibility of an acoustic liner applied to a Fenestron: experimentation." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 270, no. 9 (2024): 2265–76. http://dx.doi.org/10.3397/in_2024_3160.

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A helicopter's anti-torque system is a significant contributor to radiated noise. The Fenestron, used on Airbus Helicopters, allows to mitigate the anti-torque noise by masking effect and modulation of the blade distribution. However, unlike aircraft engine nacelles, it does not contain acoustic liners inside the duct to absorb the noise radiated by the rotor blades. This paper describes: first, the (aero-)acoustic tests applied to different acoustic liners optimised to be integrated into a 1/3-scale fenestron mock-up, in order to provide a specific impedance (measurement in impedance tube and

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Wang, Ruichen, and Xun Huang. "Sound radiation from semi-infinite elliptical ducts with uniform subsonic jets: An analytical approach." Journal of the Acoustical Society of America 154, no. 4_supplement (2023): A188—A189. http://dx.doi.org/10.1121/10.0023221.

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This paper presents an analytical method for modeling the acoustic field radiation from a semi-infinite elliptical duct with a uniform subsonic jet. Elliptical ducts are often used as inlets for turbofan engines to take full advantage of the pre-compression effect of the fuselage and improve the stealth performance of the aircraft. The method accounts for the instability wave inside the vortex sheet induced by the shearing of jet and ambient flow and its effect to sound radiation. The method uses Mathieu functions to describe the incident and scattered sound in the elliptic cylindrical coordin

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Schloesser, Philipp, Michael Meyer, Martin Schueller, Perez Weigel, and Matthias Bauer. "Fluidic actuators for separation control at the engine/wing junction." Aircraft Engineering and Aerospace Technology 89, no. 5 (2017): 709–18. http://dx.doi.org/10.1108/aeat-01-2017-0013.

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Purpose The area behind the engine/wing junction of conventional civil aircraft configurations with underwing-mounted turbofans is susceptible to local flow separation at high angles of attack, which potentially impacts maximum lift performance of the aircraft. This paper aims to present the design, testing and optimization of two distinct systems of fluidic actuation dedicated to reduce separation at the engine/wing junction. Design/methodology/approach Active flow control applied at the unprotected leading edge inboard of the engine pylon has shown considerable potential to alleviate or even

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Tesis sobre el tema "Numerical optimization and civil aircraft engine noise"

Ezzine, Mouhamed Mounibe. "Etude de dispositifs passifs et actifs de réduction du bruit d’interaction soufflante–redresseur." Electronic Thesis or Diss., Ecully, Ecole centrale de Lyon, 2024. http://www.theses.fr/2024ECDL0022.

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Deux approches de diminution du bruit d'origine aéroacoustique associé à l'OGV des moteurs d'avion ont été examinées dans cette thèse. La première repose sur des solutions passives, utilisant des matériaux comme de la mousse poreuse et du tissu métallique (wire mesh) pour atténuer le bruit. L'efficacité de ces matériaux a été testée dans diverses configurations, montrant une capacité de réduction du bruit jusqu'à 6 dB sous certaines conditions, bien que cette efficacité puisse être affectée par des facteurs comme la vitesse de l'écoulement. La seconde partie de l'étude s'est intéressée aux tec

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Actas de conferencias sobre el tema "Numerical optimization and civil aircraft engine noise"

Igor, Egorov N., Kretinin V. Gennady, Leshchenko A. Igor, and Kuptzov V. Sergey. "Multi-Objective Robust Optimization of Air Engine Using IOSO Technology." In ASME Turbo Expo 2004: Power for Land, Sea, and Air. ASMEDC, 2004. http://dx.doi.org/10.1115/gt2004-53504.

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This paper demonstrates the multi-objective optimization of air engine in aircraft system using either Deterministic or Robust Design Optimization statements. The goal is to obtain the Pareto-optimum frontier for the air engine and aircraft parameters. Performance characteristics of engine include the following: specific fuel consumption; thrust, with external resistance included, for any flight operating modes of aircraft; weight; the engine size parameters; engine’s life period; level of engine noise; and maintenance costs of the engine. Performance characteristics of an aircraft include pas

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Carnevale, Mauro, Feng Wang, and Luca di Mare. "Low Frequency Distortion in Civil Aero-Engine Intake." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56203.

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The main role of the intake is to provide a sufficient mass flow to the engine face and sufficient flow homogeneity to the fan. Intake-fan interaction off design represents a critical issue in the design process because intake lines are set very early during the aircraft optimization. The off-design operation of an aero-engine, strictly related to the intake flow field, can be mainly related to two different conditions. When the plane is in near ground position, vorticity can be ingested by the fan due to crosswind incidence. During the flight, distortions occur due to incidence. In these cond

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Shah, P. N., D. D. Mobed, and Z. S. Spakovszky. "A Novel Turbomachinery Air-Brake Concept for Quiet Aircraft." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27635.

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A novel air-brake concept for next generation, low-noise civil aircraft is introduced. Deployment of such devices in clean airframe configuration reduces aircraft source noise and noise propagation to the ground. The generation of swirling outflow from a duct, such as an aircraft engine, is demonstrated to have high drag and low noise. The simplest configuration is a ram pressure driven duct with stationary swirl vanes, a so-called swirl tube. A detailed aerodynamic design is performed using first principles based modeling and high-fidelity numerical simulations. The swirl-drag-noise relations

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Bartelt, Michael, Juan D. Laguna, and Joerg R. Seume. "Synthetic Sound Source Generation for Acoustical Measurements in Turbomachines." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95045.

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One of the greatest challenges in modern aircraft propulsion design is the reduction of the engine noise emission in order to develop quieter aircrafts. In the course of a current research project, the sound transport in low pressure turbines is investigated. For the corresponding experimental measurements, a specific acoustic excitation system is developed which can be implemented into the inlet of a turbine test rig and into an aeroacoustic wind tunnel. This allows for an acoustic mode generation and a synthesis of various sound source patterns to simulate typical turbomachinery noise source

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Fiorio, M. "Hardware-in-the-loop validation of a sense and avoid system leveraging data fusion between radar and optical sensors for a mini UAV." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-16.

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Abstract. The present work illustrates the results obtained at the conclusion of the three-year project TERSA (Tecnologie Elettriche e Radar per Sapr Autonomi), involving the aerospace section of the Dept. of Civil and Industrial Engineering (DICI) of the University of Pisa and its industrial partners. The project aimed at the design and development of a fully autonomous Sense and Avoid (SAA) prototype system, based on data fusion between optical and radar sensors data, for a tactical lightweight surveillance UAV (MTOW<25Kg). The problem of non-cooperative collision avoidance is well known

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