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Numerical Simulation of Fore and Aft Sound Fields of a Turbofan.

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Title: Numerical Simulation of Fore and Aft Sound Fields of a Turbofan.
Authors: Özyörük, Y.1 ozyoruk@metu.edu.tr, Ahuja, V.2 vineet@craft-tech.com, Atassi, H. M.
Source: AIAA Journal. Oct2004, Vol. 42 Issue 10, p2028-2034. 7p. 9 Diagrams.
Subjects: Aerodynamics, Fluid dynamics, Fluid mechanics, Turbojet helicopter engines, Turbojet plane engines, Aerospace engineering, Mathematical models, Euler characteristic, Mechanical engineering
Abstract: A framework for predicting fan related noise from high bypass ratio engines is presented. The methodology accounts for both fore and aft radiation and includes the effects of liner treatment on the engine walls. Solutions are obtained through a combination of Euler and linearized Euler solvers, coupled with a Kirchhoff formulation for far-field noise prediction. The nacelle region is solved using the Euler solver, whereas the linearized Euler solver is used for the fan exhaust stage. Switching to the linearized Euler solver in the aft region has been necessary to overcome difficulties experienced due to the coupling of the acoustic modes with flow near the engine exhaust boundary and appearance of flow instabilities in the shear layer trailing the exhaust shroud. Results are presented for spinning modes from a turbofan engine with acoustic treatment. [ABSTRACT FROM AUTHOR]
Copyright of AIAA Journal is the property of American Institute of Aeronautics & Astronautics and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
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Header DbId: egs
DbLabel: Engineering Source
An: 14795177
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
PreciseRelevancyScore: 0
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  Group: Ti
  Data: Numerical Simulation of Fore and Aft Sound Fields of a Turbofan.
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  Data: <searchLink fieldCode="AR" term="%22Özyörük%2C+Y%2E%22">Özyörük, Y.</searchLink><relatesTo>1</relatesTo><i> ozyoruk@metu.edu.tr</i><br /><searchLink fieldCode="AR" term="%22Ahuja%2C+V%2E%22">Ahuja, V.</searchLink><relatesTo>2</relatesTo><i> vineet@craft-tech.com</i><br /><searchLink fieldCode="AR" term="%22Atassi%2C+H%2E+M%2E%22">Atassi, H. M.</searchLink>
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  Data: <searchLink fieldCode="JN" term="%22AIAA+Journal%22">AIAA Journal</searchLink>. Oct2004, Vol. 42 Issue 10, p2028-2034. 7p. 9 Diagrams.
– Name: Subject
  Label: Subjects
  Group: Su
  Data: <searchLink fieldCode="DE" term="%22Aerodynamics%22">Aerodynamics</searchLink><br /><searchLink fieldCode="DE" term="%22Fluid+dynamics%22">Fluid dynamics</searchLink><br /><searchLink fieldCode="DE" term="%22Fluid+mechanics%22">Fluid mechanics</searchLink><br /><searchLink fieldCode="DE" term="%22Turbojet+helicopter+engines%22">Turbojet helicopter engines</searchLink><br /><searchLink fieldCode="DE" term="%22Turbojet+plane+engines%22">Turbojet plane engines</searchLink><br /><searchLink fieldCode="DE" term="%22Aerospace+engineering%22">Aerospace engineering</searchLink><br /><searchLink fieldCode="DE" term="%22Mathematical+models%22">Mathematical models</searchLink><br /><searchLink fieldCode="DE" term="%22Euler+characteristic%22">Euler characteristic</searchLink><br /><searchLink fieldCode="DE" term="%22Mechanical+engineering%22">Mechanical engineering</searchLink>
– Name: Abstract
  Label: Abstract
  Group: Ab
  Data: A framework for predicting fan related noise from high bypass ratio engines is presented. The methodology accounts for both fore and aft radiation and includes the effects of liner treatment on the engine walls. Solutions are obtained through a combination of Euler and linearized Euler solvers, coupled with a Kirchhoff formulation for far-field noise prediction. The nacelle region is solved using the Euler solver, whereas the linearized Euler solver is used for the fan exhaust stage. Switching to the linearized Euler solver in the aft region has been necessary to overcome difficulties experienced due to the coupling of the acoustic modes with flow near the engine exhaust boundary and appearance of flow instabilities in the shear layer trailing the exhaust shroud. Results are presented for spinning modes from a turbofan engine with acoustic treatment. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of AIAA Journal is the property of American Institute of Aeronautics & Astronautics and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
PLink https://search.ebscohost.com/login.aspx?direct=true&site=eds-live&db=egs&AN=14795177
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      – Code: eng
        Text: English
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        PageCount: 7
        StartPage: 2028
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      – SubjectFull: Aerodynamics
        Type: general
      – SubjectFull: Fluid dynamics
        Type: general
      – SubjectFull: Fluid mechanics
        Type: general
      – SubjectFull: Turbojet helicopter engines
        Type: general
      – SubjectFull: Turbojet plane engines
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      – SubjectFull: Aerospace engineering
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      – SubjectFull: Mathematical models
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      – SubjectFull: Euler characteristic
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      – SubjectFull: Mechanical engineering
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      – TitleFull: Numerical Simulation of Fore and Aft Sound Fields of a Turbofan.
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            NameFull: Ahuja, V.
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            NameFull: Atassi, H. M.
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              Text: Oct2004
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