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CFD Computation of Broadband Fan Interaction NoiseIn this study, a 3-D, unsteady, Reynolds Averaged Navier Stokes CFD code coupled to an acoustic calculation is used to predict the contribution of the exit guide vanes to broadband fan noise. The configuration investigated is that corresponding to the NASA Source Diagnostic Test (SDT) 22-in fan rig. Then an acoustic model introduced by Nallasamy which is based on 2-D strip theory is used to compute the broadband rotor-stator interaction noise. One configuration from the SDT matrix is considered here: the fan speed correlating to approach, and outlet guide vane count designed for cut-off of the blade passage frequency. Thus, in the chosen configuration, there are 22 rotor blades and 54 stator blades. The stators are located 2.5 tip chords downstream of the rotor trailing edge. The RANS computations are used to obtain the spectra of the unsteady surface pressure on the exit guide vanes. This surface pressure is then integrated together with the Green's function for and infinite cylindrical duct to obtain the acoustic field. The results from this investigation validate the use of the CFD code along with the acoustic model for broadband fan noise predictions. The validation enables future investigations such as the determination of rotor tip clearance and stator solidity effects on fan rotor-stator interaction noise.
Document ID
20080013319
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Grace, Sheryl M.
(Boston Univ. Boston, MA, United States)
Sondak, Douglas L.
(Boston Univ. Boston, MA, United States)
Dorney, Daniel J.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 24, 2013
Publication Date
November 10, 2007
Subject Category
Acoustics
Report/Patent Number
IMECE2007-43779
Meeting Information
Meeting: 2007 ASME International Mechanical Engineering Congress and Exposition (IMECE 07)
Location: Seattle, WA
Country: United States
Start Date: November 10, 2007
End Date: November 16, 2007
Distribution Limits
Public
Copyright
Other

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