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Boundary Layer induced Rotor Noise using an Analytical Modal Approach

Staggat, M. and Guerin, S. and Moreau, A. (2016) Boundary Layer induced Rotor Noise using an Analytical Modal Approach. 22nd AIAA/CEAS Aeroacoustics Conference, 30. May - 1. June 2016, Lyon, Frankreich.

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Abstract

Upcoming aircraft designs will face new acoustic challenges related to flow distortions ingested by the engines, such as the boundary layer developing on the fuselage interacting with the fan blades. This paper presents an analytical method to predict this interaction based on the description of circumferential modes in the frequency domain. The original broadband noise model already implemented in the DLR in-house tool PropNoise has been extended to account for anisotropic turbulence and large turbulence scales. The adopted modeling approach confirms that axially stretched eddies generate bumps centered on the harmonics of the blade passing frequency. On the one hand, the small turbulent scales in circumferential direction provide a rich content in aerodynamic perturbation modes. On the other hand, large axial length scales lead to a partial correlation between several consecutive blades, where Tyler-Sofrin modes are preferably excited. The combination of both effects creates acoustic interaction modes with a low circumferential order, which is a condition for efficient sound radiation even at low frequencies. Finally, the model is applied to the academic test case FC3 of a rotor immersed in a thick boundary layer, in the framework of the “Fan Broadband Noise Prediction Workshop” organized in Dallas, 2015 and Lyon, 2016.

Item URL in elib:https://elib.dlr.de/120871/
Document Type:Conference or Workshop Item (Speech)
Title:Boundary Layer induced Rotor Noise using an Analytical Modal Approach
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Staggat, M.dlrUNSPECIFIED
Guerin, S.UNSPECIFIEDUNSPECIFIED
Moreau, A.UNSPECIFIEDUNSPECIFIED
Date:2016
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Inflow distortion, engine acoustics, aero acoustics
Event Title:22nd AIAA/CEAS Aeroacoustics Conference
Event Location:Lyon, Frankreich
Event Type:international Conference
Event Dates:30. May - 1. June 2016
Organizer:3AF
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Virtual Engine and Validation methods
Location: Berlin-Charlottenburg
Institutes and Institutions:Institute of Propulsion Technology > Engine Acoustic
Deposited By: Spitalny, Mirko
Deposited On:10 Jul 2018 09:00
Last Modified:10 Jul 2018 09:00

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