CFD Computation of Fan Interaction Noise (original) (raw)

2007, Volume 8: Heat Transfer, Fluid Flows, and Thermal Systems, Parts A and B

In this study, a 3-D, unsteady, Reynolds-averaged Navier-Stokes (RANS) CFD code coupled to an acoustic calculation is used to predict the contribution of the exit guide vanes to tonal fan noise downstream. The configuration investigated is that corresponding to the NASA Source Diagnostic Test (SDT) 22-in fan rig. One configuration from the SDT matrix is considered here: the approach condition, and outlet guide vane count designed for cutoff of the blade passage frequency. In this 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. The surface pressure at the blade passage frequency and its second harmonic are then integrated together with the Green's function for an annular duct to obtain the pressure at locations in the duct. Comparison of the computed sound power level at the exhaust plane with experiment show good agreement at the cut-on circumferential mode. The results from this investigation validate the use of the CFD code along with the acoustic model for downstream * Address all correspondence to this author. fan noise predictions. This validation enables future investigations such as the effect of duct variation on the exhaust tonal power level and the validity of using this method for predicting broadband noise levels. NOMENCLATURE β = √ 1 − M 2 compressibility parameter ω radial frequency of disturbance a outer radius of annulus c chordlength c 0 mean speed of sound h inner radius of annulus I acoustic intensity g gust amplitude, 2D benchmark simulation G Green's function J n ,Y n Bessel functions of order n k = ω/c 0 acoustic wave number k 1 , k 2 nondimensional wave numbers of 2D gust K nm eigenfrequencies of propagation M Mach number 1 Copyright c 2007 by ASME p pressure P acoustic power q, s integers, multipliers of B and V r h , r t , r radial location of rotor hub, tip, strip u acoustic velocity in the axial direction (x, y, z), (r, θ, z) point in space x 0 = (r 0 , θ 0 , z 0) source locations