Predictions of rotor alone tones in a transonic fan using steady CFD

I. D J Dupére; W. N. Dawes; A. G. Wilson; B. J. Tester

Predictions of rotor alone tones in a transonic fan using steady CFD

I. D J Dupére, W. N. Dawes, A. G. Wilson, B. J. Tester

Research output: Chapter in Book/Conference proceeding › Conference contribution

Abstract

At transonic speeds in fans, the circumferential variation in the pressure due to shock waves and expansion fans constitutes a significant part of the sound field in the intake duct as it rotates relative to a stationary observer. Unlike low amplitude sound waves at lower speeds, the resulting waves propagate in a non-linear fashion, decaying as they propagate upstream. Since these tones are the same as the flow field which is steady relative to the blades, they are susceptible to prediction using standard steady (relative to the blades) CFD solvers. Predictions for a fan blade across a range of fan speeds and over a range of working conditions are given here with comparison with experimental measurements made on the same fan. The agreement is within 3dB in most cases, provided a sufficiently fine mesh is used all the way along the inlet duct and provided pseudo non-reflecting boundary conditions are used.

Original language	English
Title of host publication	39th Aerospace Sciences Meeting and Exhibit\|39th Aerosp. Sci. Meet. Exhibit
Publication status	Published - 2001
Event	39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV Duration: 1 Jul 2001 → …

Conference

Conference	39th Aerospace Sciences Meeting and Exhibit 2001
City	Reno, NV
Period	1/07/01 → …

Cite this

@inproceedings{d040747dc3d84dccaaddfaf56268a682,

title = "Predictions of rotor alone tones in a transonic fan using steady CFD",

abstract = "At transonic speeds in fans, the circumferential variation in the pressure due to shock waves and expansion fans constitutes a significant part of the sound field in the intake duct as it rotates relative to a stationary observer. Unlike low amplitude sound waves at lower speeds, the resulting waves propagate in a non-linear fashion, decaying as they propagate upstream. Since these tones are the same as the flow field which is steady relative to the blades, they are susceptible to prediction using standard steady (relative to the blades) CFD solvers. Predictions for a fan blade across a range of fan speeds and over a range of working conditions are given here with comparison with experimental measurements made on the same fan. The agreement is within 3dB in most cases, provided a sufficiently fine mesh is used all the way along the inlet duct and provided pseudo non-reflecting boundary conditions are used.",

author = "Dup{\'e}re, {I. D J} and Dawes, {W. N.} and Wilson, {A. G.} and Tester, {B. J.}",

year = "2001",

language = "English",

booktitle = "39th Aerospace Sciences Meeting and Exhibit|39th Aerosp. Sci. Meet. Exhibit",

note = "39th Aerospace Sciences Meeting and Exhibit 2001 ; Conference date: 01-07-2001",

}

TY - GEN

T1 - Predictions of rotor alone tones in a transonic fan using steady CFD

AU - Dupére, I. D J

AU - Dawes, W. N.

AU - Wilson, A. G.

AU - Tester, B. J.

PY - 2001

Y1 - 2001

N2 - At transonic speeds in fans, the circumferential variation in the pressure due to shock waves and expansion fans constitutes a significant part of the sound field in the intake duct as it rotates relative to a stationary observer. Unlike low amplitude sound waves at lower speeds, the resulting waves propagate in a non-linear fashion, decaying as they propagate upstream. Since these tones are the same as the flow field which is steady relative to the blades, they are susceptible to prediction using standard steady (relative to the blades) CFD solvers. Predictions for a fan blade across a range of fan speeds and over a range of working conditions are given here with comparison with experimental measurements made on the same fan. The agreement is within 3dB in most cases, provided a sufficiently fine mesh is used all the way along the inlet duct and provided pseudo non-reflecting boundary conditions are used.

AB - At transonic speeds in fans, the circumferential variation in the pressure due to shock waves and expansion fans constitutes a significant part of the sound field in the intake duct as it rotates relative to a stationary observer. Unlike low amplitude sound waves at lower speeds, the resulting waves propagate in a non-linear fashion, decaying as they propagate upstream. Since these tones are the same as the flow field which is steady relative to the blades, they are susceptible to prediction using standard steady (relative to the blades) CFD solvers. Predictions for a fan blade across a range of fan speeds and over a range of working conditions are given here with comparison with experimental measurements made on the same fan. The agreement is within 3dB in most cases, provided a sufficiently fine mesh is used all the way along the inlet duct and provided pseudo non-reflecting boundary conditions are used.

M3 - Conference contribution

BT - 39th Aerospace Sciences Meeting and Exhibit|39th Aerosp. Sci. Meet. Exhibit

T2 - 39th Aerospace Sciences Meeting and Exhibit 2001

Y2 - 1 July 2001

ER -

Predictions of rotor alone tones in a transonic fan using steady CFD

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