Fan Noise Source Diagnostic Test- LDV Measured Flow Field Results

Podboy, Gary C.; Krupar, Martin J.; Hughes, Christopher E.; Woodward, Richard P.

doi:10.2514/6.2002-2431

Cited by 56 publications

(25 citation statements)

References 4 publications

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“…Significant overall broadband levels are radiated to the far field due to motion and stretching of turbulent flow eddies 1,2 . In addition, generally intense tonal noise at specific frequencies as a result of rotor-stator interaction coupled with duct mode propagation in the nacelle is observed [2][3][4][5][6][7][8][9] . In the past decade, an effort towards the development of efficient acoustics liner aiming to reduce mainly the tonal part of the noise has been carried out.…”

Section: Introductionmentioning

confidence: 99%

“…A method allowing accurate modal decomposition as well as a good estimation of overall broadband content is therefore required. The Advance Noise Control Fan (ANCF) geometry of the NASA Glenn Research Center was developed in the early 1990's to provide detailed measurements of a turbo fan flow and corresponding noise produced by the ducted rotor/stator [2][3][4][5][6][7][8][9]12,13 . The measurements provide a better understanding of the correlation between the flow and the propagation inside the duct as well as the radiation to the far field.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Advanced Noise Control Fan Direct Aeroacoustics Predictions Using a Lattice-Boltzmann Method

Mann¹,

Pérot²,

Kim³

et al. 2012

18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)

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A Lattice-Boltzmann Method (LBM) based approach is used to perform transient, explicit and compressible CFD/CAA simulations on the Advanced Noise Control Fan (ANCF) configuration. The complete 3-D ducted rotor/stator model including all the geometrical details and the truly rotating rotor is simulated. Detailed near and far-field measurements conducted at the NASA Glenn research center are used to validate the simulation results. The measured and predicted sound pressure levels at the far-field microphones are compared and both show the presence of broadband noise and sharp peaks which frequencies depend on the number of rotor blades and the angular velocity of the rotor. The 3-D duct acoustics modes observed in experiments are also captured in the 3-D transient CFD/CAA calculation and detailed analyses of the results are presented. The main circumferential modes predicted from the number of rotor blades and stator vanes are recovered in both experimental and simulation modal decompositions. Nomenclature M = Mach number f k = k -th BPF harmonic order c b = Rotor blade chord s b = Rotor blade span Δx tip = Tip clearance c v = Stator vane chord d h,up = Upstream hub diameter d h,do = Downstream hub diameter p = Static pressure r = Radial coordinate θ = Azimuthal coordinate x = Axis coordinate t = Time m = Circumferential mode order n = Radial mode order k = x-axis eigenvalue κ = radial eigenvalue J m = Bessel function of the first kind and order m B = Number of fan blades V = Number of stator vanes s = Fan shaft harmonic Ω = Rotation frequency of the fan c 0 2 R 0 = Fan radius ρ 0 = Air density C i = Discrete collision component in the i -th direction c i = Discrete velocity component in the i -th direction f i = Particle distribution function in the i -th direction T = Temperature τ = Relaxation time ν = Kinematic viscosity ∆t = Numerical time step

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Advanced Noise Control Fan Direct Aeroacoustics Predictions Using a Lattice-Boltzmann Method

Mann¹,

Pérot²,

Kim³

et al. 2012

18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)

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“…Recent aircraft engine noise research by NASA and the aerospace industry [1][2][3][4][5] has focused on identifying the composition of the noise sources in a modern turbofan aircraft engine, their generation mechanisms, and the level of contribution to the total aircraft system noise level. A test was conducted in the NASA Glenn Research Center 9-by 15-Foot Low Speed Wind Tunnel (9x15 LSWT), called the Source Diagnostic Test.…”

Section: Introductionmentioning

confidence: 99%

Fan Noise Source Diagnostic Test - Rotor Alone Aerodynamic Performance Results

Hughes¹,

Jeracki²,

Woodward³

et al. 2002

8th AIAA/CEAS Aeroacoustics Conference &Amp;amp; Exhibit

Self Cite

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“…These conditions correspond to the SDT baseline configuration test at approach (7808 RPM), at a radial location of 8.8 inches. 21 The incoming flow angle is 33.66 • with respect to the x-direction. A frequency of 5726 Hz was used for all incoming acoustic waves; this corresponds to twice the blade passing frequency.…”

Section: Description Of Test Casesmentioning

confidence: 99%

Computational Aeroacoustics Prediction of Acoustic Transmission Through a Realistic 2D Stator

Hixon

2011

17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)

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Fan Noise Source Diagnostic Test- LDV Measured Flow Field Results

Cited by 56 publications

References 4 publications

Advanced Noise Control Fan Direct Aeroacoustics Predictions Using a Lattice-Boltzmann Method

Advanced Noise Control Fan Direct Aeroacoustics Predictions Using a Lattice-Boltzmann Method

Fan Noise Source Diagnostic Test - Rotor Alone Aerodynamic Performance Results

Computational Aeroacoustics Prediction of Acoustic Transmission Through a Realistic 2D Stator

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