Sound Radiation from a Generic Bypass Duct with Bifurcations

Abstract

The influence of bifurcations in an aero-engine bypass duct on noise radiation was investigated through high-order accurate three-dimensional numerical simulations. The physical process was described by a set of acoustic perturbation equations (APE), with a background mean flow. Four bifurcation arrangements, with an airfoil cross-section, were regularly placed in circumferential direction. Results of the simulations were compared with those of a clean duct case. A circumferential mode of m=12 with radial mode of n=1 and multi-n modes at a source frequency of 1547 Hz were set as acoustic inputs. For single radial mode case, acoustic modes interfered with the bifurcations resulting in a doubled circumferential mode pattern in the near field acoustic pressure distribution. Far field noise computations indicated 3.2 dB and 2.0 dB sound pressure level increases for radial mode of n=1 and multi-n modes respectively. A comparison was also made between APE and linearlised Euler equations (LEE). Results showed that the APE simulation produced almost identical far field sound prediction to the LEE, with a small difference (< 0.8dB) at the main radiation peak angle.

Evaluation and Development of Non-Reflective Boundary Conditions for Aeroacoustic Simulations

“…A circumferential mode number of m = 12 was used, and the frequency of the disturbance was 1500 Hz. This configuration was previously studied by Chen et al 36 The disturbance was injected at the domain inflow and allowed to propagate over a non-uniform meanflow solution that was obtained with a RANS calculation using a commercial steady flow solver. To reduce the computational cost, a 1/12th segment of the engine was simulated and periodic conditions were applied.…”