Effects of nozzle configuration and bypass ratio on the aeroacoustics of dual stream supersonic jets

Scott M. Hromisin, Dennis K. McLaughlin, Philip J. Morris

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

Abstract

Multi-stream, variable cycle point, low bypass ratio, turbofan engines are in consideration for future tactical aircraft. Such engine architectures aim to cycle between high-thrust and high-efficiency operation as required by the demands of the flight profile. There exists a need to improve the understanding of the aeroacoustic characteristics of low bypass ratio, multi-stream exhaust jets. This work reports on far field acoustic measurements of heat-simulated, supersonic jets exhausting from small-scale dual stream, rectangular nozzles. Comparisons are made to elucidate the effects of bypass ratio on the radiated noise. Comparisons are made on a combined constant mass flow rate and constant estimated thrust basis. Data are compared with far field noise measurements of an asymmetric, dual stream circular jet operating at the same total pressures and (simulated) total temperatures. The results of acoustic measurements indicate how components of the noise are influenced by the flow geometry and changes in dual stream nozzle operating conditions.

Original languageEnglish (US)
Title of host publication25th AIAA/CEAS Aeroacoustics Conference, 2019
Publisher[publishername] American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105883
DOIs
StatePublished - Jan 1 2019
Event25th AIAA/CEAS Aeroacoustics Conference, 2019 - Delft, Netherlands
Duration: May 20 2019May 23 2019

Publication series

Name25th AIAA/CEAS Aeroacoustics Conference, 2019

Conference

Conference25th AIAA/CEAS Aeroacoustics Conference, 2019
CountryNetherlands
CityDelft
Period5/20/195/23/19

Fingerprint

bypass ratio
Bypass ratio
Aeroacoustics
aeroacoustics
nozzles
Nozzles
Acoustic field measurement
configurations
acoustic measurement
Turbofan engines
far fields
Acoustic noise
turbofan engines
high thrust
exhausting
flow geometry
Acoustics
Aircraft
Flow rate
cycles

All Science Journal Classification (ASJC) codes

  • Acoustics and Ultrasonics
  • Electrical and Electronic Engineering
  • Aerospace Engineering

Cite this

Hromisin, S. M., McLaughlin, D. K., & Morris, P. J. (2019). Effects of nozzle configuration and bypass ratio on the aeroacoustics of dual stream supersonic jets. In 25th AIAA/CEAS Aeroacoustics Conference, 2019 (25th AIAA/CEAS Aeroacoustics Conference, 2019). [publishername] American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2019-2766
Hromisin, Scott M. ; McLaughlin, Dennis K. ; Morris, Philip J. / Effects of nozzle configuration and bypass ratio on the aeroacoustics of dual stream supersonic jets. 25th AIAA/CEAS Aeroacoustics Conference, 2019. [publishername] American Institute of Aeronautics and Astronautics Inc, AIAA, 2019. (25th AIAA/CEAS Aeroacoustics Conference, 2019).
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Hromisin, SM, McLaughlin, DK & Morris, PJ 2019, Effects of nozzle configuration and bypass ratio on the aeroacoustics of dual stream supersonic jets. in 25th AIAA/CEAS Aeroacoustics Conference, 2019. 25th AIAA/CEAS Aeroacoustics Conference, 2019, [publishername] American Institute of Aeronautics and Astronautics Inc, AIAA, 25th AIAA/CEAS Aeroacoustics Conference, 2019, Delft, Netherlands, 5/20/19. https://doi.org/10.2514/6.2019-2766

Effects of nozzle configuration and bypass ratio on the aeroacoustics of dual stream supersonic jets. / Hromisin, Scott M.; McLaughlin, Dennis K.; Morris, Philip J.

25th AIAA/CEAS Aeroacoustics Conference, 2019. [publishername] American Institute of Aeronautics and Astronautics Inc, AIAA, 2019. (25th AIAA/CEAS Aeroacoustics Conference, 2019).

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

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Hromisin SM, McLaughlin DK, Morris PJ. Effects of nozzle configuration and bypass ratio on the aeroacoustics of dual stream supersonic jets. In 25th AIAA/CEAS Aeroacoustics Conference, 2019. [publishername] American Institute of Aeronautics and Astronautics Inc, AIAA. 2019. (25th AIAA/CEAS Aeroacoustics Conference, 2019). https://doi.org/10.2514/6.2019-2766