Numerical simulations for supersonic jet noise reduction using fluidic inserts

Matthew Kapusta, Russell Powers, Philip J. Morris, Dennis K. McLaughlin

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

9 Citations (Scopus)

Abstract

This paper describes a computational and experimental study of the flow field in a supersonic nozzle flow including the effects of fluidic inserts. Fluidic inserts involve carefully directed blowing in the diverging section of a convergent divergent nozzle. This blowing changes the effective area ratio of the nozzle and also generates streamwise vorticity. As in the case of corrugated seal inserts, these modifications to the jet flow reduce the broadband shock-associated noise and also reduce the noise in the peak noise radiation direction. The focus of the present paper is on the flow field generated by the fluidic inserts rather than the changes in the radiated noise, which are reported elsewhere. Reynolds-Averaged Navier-Stokes simulations using a two-equation turbulence model are performed. The simulations are compared with flow measurements with a Laser Doppler Velocimeter. Flow predictions are made for a nozzle with three fluidic inserts, each generated by two injectors. An overexpanded jet operating condition is considered with and without core flow heating. The effects of different injector pressure ratios are examined. The distributions of Mach number, turbulent kinetic energy, total temperature, and streamwise vorticity are used to describe the features of the fluidic inserts. Though there are strong similarities between the effect on the core flow of the fluidic inserts and hard-walled corrugated seals, some interesting differences are identified. For example, the streamwise vortices in the hard-walled case are found in the corners of the corrugations, whereas for the fluidic inserts the vortices are confined to the interior of the corrugation.

Original languageEnglish (US)
Title of host publication54th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103933
StatePublished - Jan 1 2016
Event54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States
Duration: Jan 4 2016Jan 8 2016

Publication series

Name54th AIAA Aerospace Sciences Meeting

Other

Other54th AIAA Aerospace Sciences Meeting, 2016
CountryUnited States
CitySan Diego
Period1/4/161/8/16

Fingerprint

Fluidics
Noise abatement
Computer simulation
Nozzles
Blow molding
Vorticity
Seals
Flow fields
Vortex flow
Laser Doppler velocimeters
Flow measurement
Turbulence models
Kinetic energy
Mach number
Radiation
Heating

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Kapusta, M., Powers, R., Morris, P. J., & McLaughlin, D. K. (2016). Numerical simulations for supersonic jet noise reduction using fluidic inserts. In 54th AIAA Aerospace Sciences Meeting (54th AIAA Aerospace Sciences Meeting). American Institute of Aeronautics and Astronautics Inc, AIAA.
Kapusta, Matthew ; Powers, Russell ; Morris, Philip J. ; McLaughlin, Dennis K. / Numerical simulations for supersonic jet noise reduction using fluidic inserts. 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. (54th AIAA Aerospace Sciences Meeting).
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Kapusta, M, Powers, R, Morris, PJ & McLaughlin, DK 2016, Numerical simulations for supersonic jet noise reduction using fluidic inserts. in 54th AIAA Aerospace Sciences Meeting. 54th AIAA Aerospace Sciences Meeting, American Institute of Aeronautics and Astronautics Inc, AIAA, 54th AIAA Aerospace Sciences Meeting, 2016, San Diego, United States, 1/4/16.

Numerical simulations for supersonic jet noise reduction using fluidic inserts. / Kapusta, Matthew; Powers, Russell; Morris, Philip J.; McLaughlin, Dennis K.

54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. (54th AIAA Aerospace Sciences Meeting).

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

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N2 - This paper describes a computational and experimental study of the flow field in a supersonic nozzle flow including the effects of fluidic inserts. Fluidic inserts involve carefully directed blowing in the diverging section of a convergent divergent nozzle. This blowing changes the effective area ratio of the nozzle and also generates streamwise vorticity. As in the case of corrugated seal inserts, these modifications to the jet flow reduce the broadband shock-associated noise and also reduce the noise in the peak noise radiation direction. The focus of the present paper is on the flow field generated by the fluidic inserts rather than the changes in the radiated noise, which are reported elsewhere. Reynolds-Averaged Navier-Stokes simulations using a two-equation turbulence model are performed. The simulations are compared with flow measurements with a Laser Doppler Velocimeter. Flow predictions are made for a nozzle with three fluidic inserts, each generated by two injectors. An overexpanded jet operating condition is considered with and without core flow heating. The effects of different injector pressure ratios are examined. The distributions of Mach number, turbulent kinetic energy, total temperature, and streamwise vorticity are used to describe the features of the fluidic inserts. Though there are strong similarities between the effect on the core flow of the fluidic inserts and hard-walled corrugated seals, some interesting differences are identified. For example, the streamwise vortices in the hard-walled case are found in the corners of the corrugations, whereas for the fluidic inserts the vortices are confined to the interior of the corrugation.

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M3 - Conference contribution

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Kapusta M, Powers R, Morris PJ, McLaughlin DK. Numerical simulations for supersonic jet noise reduction using fluidic inserts. In 54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA. 2016. (54th AIAA Aerospace Sciences Meeting).