Noise reduction in supersonic jets by nozzle fluidic inserts

Ching Wen Kuo, Philip John Morris, Dennis K. McLaughlin

Research output: Chapter in Book/Report/Conference proceedingConference contribution

12 Citations (Scopus)

Abstract

This paper describes an innovative methodology and device for the reduction of supersonic jet noise. The goal is to develop a practical active noise reduction technique for low bypass ratio turbofan engines. This method introduces fluidic inserts installed in the divergent wall of a CD nozzle to replace hard-wall corrugation seals, which have been demonstrated to be effective by Seiner et al.1. By altering the configuration and operating conditions of the fluidic inserts, active noise reduction for both mixing and shock noise has been obtained. Substantial noise reductions have been achieved for mixing noise in the maximum noise emission direction and in the forward arc for broadband shock associated noise. To achieve these reductions (on the order of 4 and 2 dB for the two main components respectively) practically achievable levels of injection mass flow rates have been used. The total injected mass flow rates were less than 4 % of the core mass flow rate and the effective operating injection pressure ratio was maintained at or below the same level as the nozzle pressure ratio of the core flow. Refinement and optimization of this technique is being pursued at Penn State University.

Original languageEnglish (US)
Title of host publication18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)
StatePublished - Dec 1 2012
Event18th AIAA/CEAS Aeroacoustics Conference 2012 (33rd AIAA Aeroacoustics Conference) - , United States
Duration: Jun 4 2012Jun 6 2012

Publication series

Name18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)

Other

Other18th AIAA/CEAS Aeroacoustics Conference 2012 (33rd AIAA Aeroacoustics Conference)
CountryUnited States
Period6/4/126/6/12

Fingerprint

fluidics
Fluidics
inserts
Noise abatement
noise reduction
nozzles
Nozzles
mass flow rate
Flow rate
Acoustic noise
pressure ratio
Bypass ratio
Turbofan engines
bypass ratio
shock
turbofan engines
core flow
injection
jet aircraft noise
Seals

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Mechanical Engineering
  • Acoustics and Ultrasonics

Cite this

Kuo, C. W., Morris, P. J., & McLaughlin, D. K. (2012). Noise reduction in supersonic jets by nozzle fluidic inserts. In 18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference) (18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)).
Kuo, Ching Wen ; Morris, Philip John ; McLaughlin, Dennis K. / Noise reduction in supersonic jets by nozzle fluidic inserts. 18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference). 2012. (18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)).
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Kuo, CW, Morris, PJ & McLaughlin, DK 2012, Noise reduction in supersonic jets by nozzle fluidic inserts. in 18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference). 18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference), 18th AIAA/CEAS Aeroacoustics Conference 2012 (33rd AIAA Aeroacoustics Conference), United States, 6/4/12.

Noise reduction in supersonic jets by nozzle fluidic inserts. / Kuo, Ching Wen; Morris, Philip John; McLaughlin, Dennis K.

18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference). 2012. (18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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N2 - This paper describes an innovative methodology and device for the reduction of supersonic jet noise. The goal is to develop a practical active noise reduction technique for low bypass ratio turbofan engines. This method introduces fluidic inserts installed in the divergent wall of a CD nozzle to replace hard-wall corrugation seals, which have been demonstrated to be effective by Seiner et al.1. By altering the configuration and operating conditions of the fluidic inserts, active noise reduction for both mixing and shock noise has been obtained. Substantial noise reductions have been achieved for mixing noise in the maximum noise emission direction and in the forward arc for broadband shock associated noise. To achieve these reductions (on the order of 4 and 2 dB for the two main components respectively) practically achievable levels of injection mass flow rates have been used. The total injected mass flow rates were less than 4 % of the core mass flow rate and the effective operating injection pressure ratio was maintained at or below the same level as the nozzle pressure ratio of the core flow. Refinement and optimization of this technique is being pursued at Penn State University.

AB - This paper describes an innovative methodology and device for the reduction of supersonic jet noise. The goal is to develop a practical active noise reduction technique for low bypass ratio turbofan engines. This method introduces fluidic inserts installed in the divergent wall of a CD nozzle to replace hard-wall corrugation seals, which have been demonstrated to be effective by Seiner et al.1. By altering the configuration and operating conditions of the fluidic inserts, active noise reduction for both mixing and shock noise has been obtained. Substantial noise reductions have been achieved for mixing noise in the maximum noise emission direction and in the forward arc for broadband shock associated noise. To achieve these reductions (on the order of 4 and 2 dB for the two main components respectively) practically achievable levels of injection mass flow rates have been used. The total injected mass flow rates were less than 4 % of the core mass flow rate and the effective operating injection pressure ratio was maintained at or below the same level as the nozzle pressure ratio of the core flow. Refinement and optimization of this technique is being pursued at Penn State University.

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M3 - Conference contribution

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Kuo CW, Morris PJ, McLaughlin DK. Noise reduction in supersonic jets by nozzle fluidic inserts. In 18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference). 2012. (18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)).