Fan Noise Boundary Layer Ingestion Installation Effects for NOVA Aircraft Configuration

Conference paper (2019)

Authors

G. Romani Wind Energy - Aerospace Engineering
Q. Ye Wind Energy - Aerospace Engineering
F. Avallone Wind Energy - Aerospace Engineering
D. Ragni Wind Energy - Aerospace Engineering
D. Casalino Wind Energy - Aerospace Engineering
Research Group
Aircraft Noise and Climate Effects (Aerospace Engineering) (TU Delft)
Copyright: © 2019 G. Romani, Q. Ye, F. Avallone, D. Ragni, D. Casalino
DOI: https://doi.org/10.2514/6.2019-2429
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Published Date

2019

Language

English

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Faculty

Aerospace Engineering

Department

Control & Operations

Research Group

Aircraft Noise and Climate Effects

Abstract

Aim of this paper is to investigate the effects of the turbulent flow developing over a fuselage on fan noise for Boundary Layer Ingestion (BLI) embedded propulsion systems. Such engine configurations can suffer from inlet flow distortions and ingestion of turbulence at the fan plane with consequent impact on both broadband and tonal fan noise. The analysis is performed by considering a modified version of the Low-Noise configuration of the NASA Source Diagnostic Test (SDT) integrated into the Nextgen ONERA Versatile Aircraft (NOVA) fuselage in order to reproduce the NOVA BLI configuration. The numerical flow solution is obtained by solving the explicit, transient and compressible lattice-Boltzmann equation implemented in the high-fidelity CFD/CAA solver Simulia PowerFLOW
R®. The acoustic far-field is computed by using the Ffwocs-Williams & Hawkings integral solution applied to a permeable surface encompassing the fan-stage. Simulations are performed for an operating condition representative of a take-off with power cutback. Installation effects due to the BLI configuration are quantified by comparison with an isolated configuration of the modified Low-Noise SDT fan-stage geometry at same operating conditions. Comparisons are carried out in terms of fan-stage intake/interstage velocity fields, fan blades section air-loads and far-field noise; correlations between the fan-stage velocity field and noise emission for the BLI configuration are outlined. It is found that the BLI fan-stage is characterized by strong azimuthal fan blade loading unsteadiness, less periodic and coherent rotor wake tangential velocity variations and higher levels of in-plane velocity fluctuations compared to the isolated engine, resulting in far-field noise spectra with no distinct tonal components and higher broadband levels. This study represents the first high-fidelity CFD/CAA simulation of a full-scale aircraft geometry comprehensive of a BLI fan/Outlet Guide Vane (OGV) stage.

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