TY - JOUR
T1 - Steady active control of noise radiation from highly heated supersonic jets
AU - Prasad, Chitrarth
AU - Morris, Philip J.
N1 - Funding Information:
This work was performed in part under the sponsorship of the Office of Naval Research with Contract No. N00014-14-C-0157 and Dr. K. Millsaps serving as Project Monitor. The views and conclusions contained herein are those of the authors and do not represent the opinion of the Office of Naval Research or the U.S. government. The authors are grateful for the use of the experimental data collected by the Penn State research team led by Professor D. K. McLaughlin. The authors are also grateful to Dr. Jessica Morgan and Dr. Scott Hromisin for discussions on thrust calculations.
Publisher Copyright:
© 2021 Acoustical Society of America.
PY - 2021/2/1
Y1 - 2021/2/1
N2 - The goal of the present investigation is to study the effect of using fluid inserts for noise control at high exhaust temperatures by performing a sequence of large eddy simulations on a typical military-style nozzle, both with and without fluid inserts, at jet inlet total temperature ratios of 2.5, 5, and 7. An exact physics-based splitting of the jet flow-field into its hydrodynamic, acoustic, and thermal components reveals clear evidence of a reduction in the radiation efficiency of Mach waves from the controlled jet. This effect is far more pronounced at afterburner conditions, where the location of the maximum noise reduction is observed to shift upstream with increase in jet temperature, thus matching the maximum location of the jet OASPL directivity. Moreover, the maximum noise reduction achieved at afterburner conditions exceeds that obtained at lower exhaust temperatures. This is encouraging and shows that the effectiveness of the fluid inserts improves with an increase in jet exhaust temperature. Furthermore, by accounting for the effect of bleeding off bypass air for the fluid inserts in the LES simulation, this noise reduction is predicted to be achieved at a conservative thrust loss estimate of under 2% at both laboratory and afterburner operating conditions.
AB - The goal of the present investigation is to study the effect of using fluid inserts for noise control at high exhaust temperatures by performing a sequence of large eddy simulations on a typical military-style nozzle, both with and without fluid inserts, at jet inlet total temperature ratios of 2.5, 5, and 7. An exact physics-based splitting of the jet flow-field into its hydrodynamic, acoustic, and thermal components reveals clear evidence of a reduction in the radiation efficiency of Mach waves from the controlled jet. This effect is far more pronounced at afterburner conditions, where the location of the maximum noise reduction is observed to shift upstream with increase in jet temperature, thus matching the maximum location of the jet OASPL directivity. Moreover, the maximum noise reduction achieved at afterburner conditions exceeds that obtained at lower exhaust temperatures. This is encouraging and shows that the effectiveness of the fluid inserts improves with an increase in jet exhaust temperature. Furthermore, by accounting for the effect of bleeding off bypass air for the fluid inserts in the LES simulation, this noise reduction is predicted to be achieved at a conservative thrust loss estimate of under 2% at both laboratory and afterburner operating conditions.
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U2 - 10.1121/10.0003570
DO - 10.1121/10.0003570
M3 - Article
C2 - 33639803
AN - SCOPUS:85101562882
VL - 149
SP - 1306
EP - 1317
JO - Journal of the Acoustical Society of America
JF - Journal of the Acoustical Society of America
SN - 0001-4966
IS - 2
ER -