Numerical study of transonic blade-vortex interaction noise

San-Yih Lin, Yan Shin Chin

Research output: Contribution to conferencePaper

Abstract

Reduction of noise due to transonic blade-vortex interaction is investigated numerically. The near and mid-field flow fields are obtained by an Euler solver. The Euler solver is based on a third-order upwind finite-volume scheme in space and a second-order explicit Runge-Kutta scheme in time. Far field noise is then obtained from the Kirchhoff method. In this paper, we attempt to reduce two dominant sound waves, transonic and compressibility, in the transonic BVI noise. Two control techniques used are the blowing/suction and porous wall on the airfoil surface. Numerical results indicate that the blowing/suction control technique reduces the fluctuations generated by the transonic wave but has little influence on the compressibility wave unless it is employed at the leading edge of the blade. As for the surface porosity control, the results are satisfactory on reduction of both the compressibility and transonic waves.

Original languageEnglish
Pages71-76
Number of pages6
Publication statusPublished - 1995 Dec 1
EventProceedings of the 1995 ASME/JSME Fluids Engineering and Laser Anemometry Conference and Exhibition - Hilton Head, SC, USA
Duration: 1995 Aug 131995 Aug 18

Other

OtherProceedings of the 1995 ASME/JSME Fluids Engineering and Laser Anemometry Conference and Exhibition
CityHilton Head, SC, USA
Period95-08-1395-08-18

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Compressibility
Vortex flow
Blow molding
Airfoils
Flow fields
Porosity
Acoustic waves

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Lin, S-Y., & Chin, Y. S. (1995). Numerical study of transonic blade-vortex interaction noise. 71-76. Paper presented at Proceedings of the 1995 ASME/JSME Fluids Engineering and Laser Anemometry Conference and Exhibition, Hilton Head, SC, USA, .
Lin, San-Yih ; Chin, Yan Shin. / Numerical study of transonic blade-vortex interaction noise. Paper presented at Proceedings of the 1995 ASME/JSME Fluids Engineering and Laser Anemometry Conference and Exhibition, Hilton Head, SC, USA, .6 p.
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Lin, S-Y & Chin, YS 1995, 'Numerical study of transonic blade-vortex interaction noise' Paper presented at Proceedings of the 1995 ASME/JSME Fluids Engineering and Laser Anemometry Conference and Exhibition, Hilton Head, SC, USA, 95-08-13 - 95-08-18, pp. 71-76.

Numerical study of transonic blade-vortex interaction noise. / Lin, San-Yih; Chin, Yan Shin.

1995. 71-76 Paper presented at Proceedings of the 1995 ASME/JSME Fluids Engineering and Laser Anemometry Conference and Exhibition, Hilton Head, SC, USA, .

Research output: Contribution to conferencePaper

TY - CONF

T1 - Numerical study of transonic blade-vortex interaction noise

AU - Lin, San-Yih

AU - Chin, Yan Shin

PY - 1995/12/1

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N2 - Reduction of noise due to transonic blade-vortex interaction is investigated numerically. The near and mid-field flow fields are obtained by an Euler solver. The Euler solver is based on a third-order upwind finite-volume scheme in space and a second-order explicit Runge-Kutta scheme in time. Far field noise is then obtained from the Kirchhoff method. In this paper, we attempt to reduce two dominant sound waves, transonic and compressibility, in the transonic BVI noise. Two control techniques used are the blowing/suction and porous wall on the airfoil surface. Numerical results indicate that the blowing/suction control technique reduces the fluctuations generated by the transonic wave but has little influence on the compressibility wave unless it is employed at the leading edge of the blade. As for the surface porosity control, the results are satisfactory on reduction of both the compressibility and transonic waves.

AB - Reduction of noise due to transonic blade-vortex interaction is investigated numerically. The near and mid-field flow fields are obtained by an Euler solver. The Euler solver is based on a third-order upwind finite-volume scheme in space and a second-order explicit Runge-Kutta scheme in time. Far field noise is then obtained from the Kirchhoff method. In this paper, we attempt to reduce two dominant sound waves, transonic and compressibility, in the transonic BVI noise. Two control techniques used are the blowing/suction and porous wall on the airfoil surface. Numerical results indicate that the blowing/suction control technique reduces the fluctuations generated by the transonic wave but has little influence on the compressibility wave unless it is employed at the leading edge of the blade. As for the surface porosity control, the results are satisfactory on reduction of both the compressibility and transonic waves.

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Lin S-Y, Chin YS. Numerical study of transonic blade-vortex interaction noise. 1995. Paper presented at Proceedings of the 1995 ASME/JSME Fluids Engineering and Laser Anemometry Conference and Exhibition, Hilton Head, SC, USA, .