Fan Noise Boundary Layer Ingestion Installation Effects for NOVA Aircraft Configuration

Gianluca Romani; Qingqing Ye; Francesco Avallone; Daniele Ragni; Damiano Casalino

doi:10.2514/6.2019-2429

Fan Noise Boundary Layer Ingestion Installation Effects for NOVA Aircraft Configuration

Gianluca Romani, Qingqing Ye, Francesco Avallone, Daniele Ragni, Damiano Casalino

Wind Energy

Research output: Chapter in Book/Conference proceedings/Edited volume › Conference contribution › Scientific › peer-review

6 Citations (Scopus)

130 Downloads (Pure)

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.

Original language	English
Title of host publication	25th AIAA/CEAS Aeroacoustics Conference
Subtitle of host publication	20-23 May 2019 Delft, The Netherlands
Publisher	American Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages	19
ISBN (Electronic)	978-1-62410-588-3
DOIs	https://doi.org/10.2514/6.2019-2429
Publication status	Published - 2019
Event	25th AIAA/CEAS Aeroacoustics Conference - Delft, Netherlands Duration: 20 May 2019 → 23 May 2019 Conference number: 25 https://arc.aiaa.org/doi/book/10.2514/MAERO19

Conference

Conference	25th AIAA/CEAS Aeroacoustics Conference
Country/Territory	Netherlands
City	Delft
Period	20/05/19 → 23/05/19
Internet address	https://arc.aiaa.org/doi/book/10.2514/MAERO19

Bibliographical note

Green Open Access added to TU Delft Institutional Repository ‘You share, we take care!’ – Taverne project https://www.openaccess.nl/en/you-share-we-take-care Otherwise as indicated in the copyright section: the publisher is the copyright holder of this work and the author uses the Dutch legislation to make this work public.

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@inproceedings{7431c31615114d8f95e720a392e310fe,

title = "Fan Noise Boundary Layer Ingestion Installation Effects for NOVA Aircraft Configuration",

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{\textregistered}. 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. ",

author = "Gianluca Romani and Qingqing Ye and Francesco Avallone and Daniele Ragni and Damiano Casalino",

note = "Green Open Access added to TU Delft Institutional Repository {\textquoteleft}You share, we take care!{\textquoteright} – Taverne project https://www.openaccess.nl/en/you-share-we-take-care Otherwise as indicated in the copyright section: the publisher is the copyright holder of this work and the author uses the Dutch legislation to make this work public.; 25th AIAA/CEAS Aeroacoustics Conference ; Conference date: 20-05-2019 Through 23-05-2019",

year = "2019",

doi = "10.2514/6.2019-2429",

language = "English",

booktitle = "25th AIAA/CEAS Aeroacoustics Conference",

publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

address = "United States",

url = "https://arc.aiaa.org/doi/book/10.2514/MAERO19",

}

Romani, G, Ye, Q, Avallone, F , Ragni, D & Casalino, D 2019, Fan Noise Boundary Layer Ingestion Installation Effects for NOVA Aircraft Configuration. in 25th AIAA/CEAS Aeroacoustics Conference: 20-23 May 2019 Delft, The Netherlands., AIAA 2019-2429, American Institute of Aeronautics and Astronautics Inc. (AIAA), 25th AIAA/CEAS Aeroacoustics Conference, Delft, Netherlands, 20/05/19. https://doi.org/10.2514/6.2019-2429

Fan Noise Boundary Layer Ingestion Installation Effects for NOVA Aircraft Configuration. / Romani, Gianluca; Ye, Qingqing; Avallone, Francesco et al.
25th AIAA/CEAS Aeroacoustics Conference: 20-23 May 2019 Delft, The Netherlands. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2019. AIAA 2019-2429.

Research output: Chapter in Book/Conference proceedings/Edited volume › Conference contribution › Scientific › peer-review

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T1 - Fan Noise Boundary Layer Ingestion Installation Effects for NOVA Aircraft Configuration

AU - Romani, Gianluca

AU - Ye, Qingqing

AU - Avallone, Francesco

AU - Ragni, Daniele

AU - Casalino, Damiano

N1 - Conference code: 25

PY - 2019

Y1 - 2019

N2 - 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.

AB - 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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U2 - 10.2514/6.2019-2429

DO - 10.2514/6.2019-2429

M3 - Conference contribution

BT - 25th AIAA/CEAS Aeroacoustics Conference

PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)

T2 - 25th AIAA/CEAS Aeroacoustics Conference

Y2 - 20 May 2019 through 23 May 2019

ER -

Fan Noise Boundary Layer Ingestion Installation Effects for NOVA Aircraft Configuration

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