Finite Element-Integral Acoustic Simulation of JT15D Turbofan Engine

Baumeister, K. J.; Horowitz, S. J.

doi:10.1115/1.3269210

Cited by 13 publications

(9 citation statements)

References 13 publications

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“…A more detailed description of the JT15D inlet configuration can be found in Ref. 24. A circumferentially uniform array of 41 rods was placed in front of the 28 fan blades in order to generate a dominant spinning mode (m= -13) at the blade passage frequency (BPF).…”

Section: Resultsmentioning

confidence: 99%

A Combined Shape and Liner Optimization of a General Aeroengine Intake for Tone Noise Reduction

Qiu

Ying

2015

Procedia Engineering

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A novel acoustic design methodology for turbofan engine inlets is presented. A fan intake tonal noise propagation model is enhanced with its continuous adjoint formulation, having been first applied to design the intake. This is followed by the implement of a liner optimization study on the obtained optimal intake in which far-field noise attenuation due to the presence of a liner is maximized by adjusting the liner impedance. The dependence of optimal liner impedance on frequency is examined. The present paper aims at describing the potential of the combined shape optimization and liner optimization for low noise turbofan duct design. Prior to the optimization process, the implementation of the unsteady aeroacoustic adjoint method in shape optimization is validated by comparing the sensitivity derivative with that obtained by finite differences. The NASA flow impedance tube configuration is selected for benchmarking the time domain impedance condition (TDIBC) used in liner optimization. The examples presented demonstrate that significant noise reduction is achieved for most of the sound field by selecting the optimal shape and liner impedance. The result obtained confirms the effectiveness and efficiency of the proposed combined shape and liner optimization framework.

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Section: Resultsmentioning

confidence: 99%

A Combined Shape and Liner Optimization of a General Aeroengine Intake for Tone Noise Reduction

Qiu

Ying

2015

Procedia Engineering

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“…In such cases, direct methods of solving the algebraic system by the Gauss elimination procedure are suffi ciently effective, which has allowed this approach to be utilized by the authors of the works in this area at the end of the 1980s-beginning of the 1990s [1][2][3][4][5]. The methodology used in the indicated works corresponds to the capabilities of computers at that time.…”

Section: A a Osipov And K S Reentmentioning

confidence: 98%

Mathematical simulation of sound propagation in a flow channel with impedance walls

Osipov

Reent

2012

Acoust. Phys.

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The paper considers the specifics of calculating tonal sound propagating in a flow channel with an installed sound absorbing device. The calculation is performed on the basis of numerical integrating on lin earized nonstationary Euler equations using a code developed by the authors based on the so called discon tinuous Galerkin method. Using the linear theory of small perturbations, the effect of the sound absorbing lining of the channel walls is described with the modified value of acoustic impedance proposed by the authors, for which, under flow channel conditions, the traditional classification of the active and reactive types of lining in terms of the real and imaginary impedance values, respectively, remains valid. To stabilize the computation process, a generalized impedance boundary condition is proposed in which, in addition to the impedance value itself, some additional parameters are introduced characterizing certain fictitious prop erties of inertia and elasticity of the impedance surface.

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“…6 and a more detailed description can be found in Ref. 34. A circumferentially uniform array of 41 rods was placed in front of the 28 fan blades in order to generate a dominant spinning mode (m = À 13) at the blade passage frequency (BPF).…”

Section: Jt15d Static Testmentioning

confidence: 99%

Geometry optimization for reducing fan noise propagating from a bypass duct

Qiu¹,

Song²,

Liu³

2013

noise cont engng j

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This paper demonstrates the application of a coupled Computational Fluid Dynamics and Computational Aeroacoustics based Kriging-based optimization technique to the aeroacoustics design of an aero-engine bypass duct. In this paper, full influence of non-uniform background flows through the duct and the shear layer on sound propagation and radiation is included in the computations. The noise prediction system using 2.5D APE model is verified with a canonical case of sound propagation out of a semi-infinite duct with flow. Excellent result is obtained for the verification problem. Numerical analysis of noise radiation from a general turbofan bypass duct is then carried out. The mean flow is obtained from Reynolds Averaged Navier-Stokes solutions using the Fluent solver. The numerical difficulties present with the sheared flows in ducts are overcome by solving the 2.5D APE equations using a linearized Euler solver in time domain. In particular, the noise reduction by a geometry optimization concept is investigated. With the optimization system based on Gaussian process-based Kriging and a genetic algorithm, an axi-symmetric bypass duct is optimized successfully and effectively by using the geometry optimization procedures. Results from the optimum bypass geometry are presented, and show that 2.5 dB noise reductions can be achieved. The results show that the optimization can effectively change the noise level and the directivity pattern in the far field. © 2013 Institute of Noise Control Engineering.

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Finite Element-Integral Acoustic Simulation of JT15D Turbofan Engine

Cited by 13 publications

References 13 publications

A Combined Shape and Liner Optimization of a General Aeroengine Intake for Tone Noise Reduction

A Combined Shape and Liner Optimization of a General Aeroengine Intake for Tone Noise Reduction

Mathematical simulation of sound propagation in a flow channel with impedance walls

Geometry optimization for reducing fan noise propagating from a bypass duct

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