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Journal articles on the topic 'Numerical optimization and civil aircraft engine noise'

Author: Grafiati

Published: 9 November 2024

Last updated: 31 July 2025

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1

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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2

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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3

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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4

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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6

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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7

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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8

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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9

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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10

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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11

Shah, P. N., D. D. Mobed, and Z. S. Spakovszky. "A Novel Turbomachinery Air-Brake Concept for Quiet Aircraft." Journal of Turbomachinery 132, no. 4 (2010). http://dx.doi.org/10.1115/1.3192145.

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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 can potentially reduce 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-

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12

Chatzisavvas, Ioannis, Ilya Arsenyev, and Rene Grahnert. "Design and optimization of squirrel cage geometries in aircraft engines toward robust whole engine dynamics." Applied and Computational Mechanics 17, no. 2 (2023). http://dx.doi.org/10.24132/acm.2023.841.

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In this work, an coupled end-to-end approach for the optimization of the rotor dynamic behavior of a dual-spool aircraft engine along with fatigue life optimization of squirrel cages (SQC) is presented. A realistic model to simulate the rotor dynamics is created, where the high-pressure (HP) rotor is supported by two squirrel cages. The aim of this work is to find a robust rotor dynamics design by shifting a critical speed to higher rotational speed, and at the same time improving the squirrel cage design with respect to fatigue life. Fully automatized coupled analysis process chain is impleme

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13

Carnevale, Mauro, Feng Wang, and Luca di Mare. "Low Frequency Distortion in Civil Aero-engine Intake." Journal of Engineering for Gas Turbines and Power 139, no. 4 (2016). http://dx.doi.org/10.1115/1.4034600.

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The main role of the intake is to provide a sufficient mass flow to the engine face and a 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 offdesign 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 con

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14

Bao, Nvzi, Yehui Peng, Heying Feng, and Chenghao Yang. "Multi-objective aerodynamic optimization design of variable camber leading and trailing edge of airfoil." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, December 6, 2021, 095440622110560. http://dx.doi.org/10.1177/09544062211056012.

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Variable camber is an effective method for improving the flight efficiency of large aircraft, and has attracted the attention of researchers. This work focused on the optimization of a variable camber airfoil. First, the influences of the variable camber of the leading and trailing edges on the airfoil aerodynamic performance were investigated using a computational fluid dynamics numerical simulation. An initial database was established for a deep neural network. Second, an iterative algorithm was constructed to optimize the variable camber airfoil in terms of the rotation angle of the leading

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15

Li, Wu, and Karl Geiselhart. "Propulsion–Airframe Integration for Conceptual Redesign of a Low-Boom Supersonic Transport." Journal of Aircraft, September 3, 2023, 1–14. http://dx.doi.org/10.2514/1.c037310.

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A low-boom supersonic transport was generated in a previous low-boom multidisciplinary optimization study that used computational fluid dynamics (CFD) off-body pressure to compute the undertrack sonic boom ground signature and calibrated low-fidelity aerodynamic analyses to compute the mission performance metrics. This low-boom aircraft, referred to as the Mach 1.7 40-PAX concept, can carry 40 passengers for a low-boom overland mission with cruise Mach 1.7 for the airport pairs over the continental United States and has the potential to achieve an undertrack sonic boom ground noise level below

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