Application of Actuator Line Model for Large Eddy Simulation of Rotor Noise Control

Yann Delorme; Ronith Stanly; Steven H. Frankel; David Greenblatt

doi:https://doi.org/10.1016/j.ast.2020.106405

Application of Actuator Line Model for Large Eddy Simulation of Rotor Noise Control

Yann Delorme, Ronith Stanly, Steven H. Frankel, David Greenblatt

Mechanical Engineering

Technion - Israel Institute of Technology

Research output: Contribution to journal › Article › peer-review

Abstract

A hybrid Large Eddy Simulation (LES)/Actuator Line Model (ALM) computational approach is employed to simulate the turbulent wake of a two-bladed rotor in hover. Validations are performed for the Knight and Hefner two-bladed rotor case with comparisons to previous LES predictions using the immersed boundary method, as well as hybrid RANS-LES using the Helios code. The Ffowcs-Williams Hawkings (FWH) acoustic analogy is then used for predicting rotor noise. Predictions from the combined LES/ALM/FWH model are next validated against recent PIV wake flow and acoustic measurements for a two-bladed rotor. Finally, the LES/ALM/FWH approach is exploited to demonstrate a novel way to explore active flow control strategies to reduce rotor noise by delaying flow separation and enabling a lower rate of rotation, resulting in lower noise while maintaining thrust.

Original language	English
Article number	106405
Journal	Aerospace Science and Technology
Volume	108
DOIs	https://doi.org/10.1016/j.ast.2020.106405
State	Published - Jan 2021

Keywords

Actuator Line Model
Helicopter noise
Large Eddy Simulation
Noise control
Rotor noise
UAV noise

All Science Journal Classification (ASJC) codes

Aerospace Engineering

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https://doi.org/10.1016/j.ast.2020.106405

Cite this

@article{f7e6638e4d4d41f78fce4b936f6ba0ae,

title = "Application of Actuator Line Model for Large Eddy Simulation of Rotor Noise Control",

abstract = "A hybrid Large Eddy Simulation (LES)/Actuator Line Model (ALM) computational approach is employed to simulate the turbulent wake of a two-bladed rotor in hover. Validations are performed for the Knight and Hefner two-bladed rotor case with comparisons to previous LES predictions using the immersed boundary method, as well as hybrid RANS-LES using the Helios code. The Ffowcs-Williams Hawkings (FWH) acoustic analogy is then used for predicting rotor noise. Predictions from the combined LES/ALM/FWH model are next validated against recent PIV wake flow and acoustic measurements for a two-bladed rotor. Finally, the LES/ALM/FWH approach is exploited to demonstrate a novel way to explore active flow control strategies to reduce rotor noise by delaying flow separation and enabling a lower rate of rotation, resulting in lower noise while maintaining thrust.",

keywords = "Actuator Line Model, Helicopter noise, Large Eddy Simulation, Noise control, Rotor noise, UAV noise",

author = "Yann Delorme and Ronith Stanly and Frankel, {Steven H.} and David Greenblatt",

note = "Publisher Copyright: {\textcopyright} 2020 Elsevier Masson SAS",

year = "2021",

month = jan,

doi = "https://doi.org/10.1016/j.ast.2020.106405",

language = "الإنجليزيّة",

volume = "108",

journal = "Aerospace Science and Technology",

issn = "1270-9638",

publisher = "Elsevier Masson s.r.l.",

}

TY - JOUR

T1 - Application of Actuator Line Model for Large Eddy Simulation of Rotor Noise Control

AU - Delorme, Yann

AU - Stanly, Ronith

AU - Frankel, Steven H.

AU - Greenblatt, David

PY - 2021/1

Y1 - 2021/1

N2 - A hybrid Large Eddy Simulation (LES)/Actuator Line Model (ALM) computational approach is employed to simulate the turbulent wake of a two-bladed rotor in hover. Validations are performed for the Knight and Hefner two-bladed rotor case with comparisons to previous LES predictions using the immersed boundary method, as well as hybrid RANS-LES using the Helios code. The Ffowcs-Williams Hawkings (FWH) acoustic analogy is then used for predicting rotor noise. Predictions from the combined LES/ALM/FWH model are next validated against recent PIV wake flow and acoustic measurements for a two-bladed rotor. Finally, the LES/ALM/FWH approach is exploited to demonstrate a novel way to explore active flow control strategies to reduce rotor noise by delaying flow separation and enabling a lower rate of rotation, resulting in lower noise while maintaining thrust.

AB - A hybrid Large Eddy Simulation (LES)/Actuator Line Model (ALM) computational approach is employed to simulate the turbulent wake of a two-bladed rotor in hover. Validations are performed for the Knight and Hefner two-bladed rotor case with comparisons to previous LES predictions using the immersed boundary method, as well as hybrid RANS-LES using the Helios code. The Ffowcs-Williams Hawkings (FWH) acoustic analogy is then used for predicting rotor noise. Predictions from the combined LES/ALM/FWH model are next validated against recent PIV wake flow and acoustic measurements for a two-bladed rotor. Finally, the LES/ALM/FWH approach is exploited to demonstrate a novel way to explore active flow control strategies to reduce rotor noise by delaying flow separation and enabling a lower rate of rotation, resulting in lower noise while maintaining thrust.

KW - Actuator Line Model

KW - Helicopter noise

KW - Large Eddy Simulation

KW - Noise control

KW - Rotor noise

KW - UAV noise

UR - http://www.scopus.com/inward/record.url?scp=85097761674&partnerID=8YFLogxK

U2 - https://doi.org/10.1016/j.ast.2020.106405

DO - https://doi.org/10.1016/j.ast.2020.106405

M3 - مقالة

SN - 1270-9638

VL - 108

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

M1 - 106405

ER -

Application of Actuator Line Model for Large Eddy Simulation of Rotor Noise Control

Abstract

Keywords

All Science Journal Classification (ASJC) codes

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