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Research Papers

Reduction of Jet Impingement Noise by Addition of Swirl

[+] Author and Article Information
P. Balakrishnan

Thermodynamics and Combustion Engineering
Laboratory,
Department of Mechanical Engineering,
Indian Institute of Technology, Madras,
Chennai 600036, India
e-mail: balaaero50@gmail.com

K. Srinivasan

Professor
Mem. ASME
Thermodynamics and Combustion Engineering
Laboratory,
Department of Mechanical Engineering,
Indian Institute of Technology, Madras,
Chennai 600036, India
e-mail: ksri@iitm.ac.in

1Corresponding author.

Contributed by the Noise Control and Acoustics Division of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received March 28, 2016; final manuscript received July 28, 2016; published online September 9, 2016. Assoc. Editor: Theodore Farabee.

J. Vib. Acoust 138(6), 061013 (Sep 09, 2016) (13 pages) Paper No: VIB-16-1146; doi: 10.1115/1.4034376 History: Received March 28, 2016; Revised July 28, 2016

Experimental investigations are carried out with an objective of reducing impingement jet noise using coaxial swirl jets. Two nozzle-to-plate distances have been considered and the Mach number values ranged from 0.95 to 1.83. The vane angles of the coaxial swirlers ranged from 0 deg to 60 deg, corresponding to swirl numbers that ranged from weak to high. Flow visualization has also been conducted to understand the shock-cell structure for each case. The results indicate that swirl jets are highly efficient in the control of impingement noise. Transonic, screech, and impinging tones are completely eliminated by the swirl jets. A weak swirl seems efficient for lower Mach numbers while higher amounts of swirl are efficient at higher Mach numbers.

Copyright © 2016 by ASME
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References

Figures

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Fig. 1

Schematic of VTOL aircraft takeoff and the adverse effects

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Fig. 2

Coaxial swirl jet device (flat vane is shown here)

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Fig. 3

Flow structures of subsonic coaxial swirling impinging jet

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Fig. 4

Flow structures of supersonic coaxial swirling impinging jet

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Fig. 5

Schematic of supersonic nonswirling impinging jets and feedback loop

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Fig. 6

Layout of anechoic test facility (not to scale)

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Fig. 7

Schematic of coaxial swirl jets

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Fig. 8

Microphone trajectory and impinging plate location

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Fig. 9

Validation of OASPL for M = 1.83, h/D = 5

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Fig. 10

Far-field sound pressure level spectra for M = 0.95 and EA 130 deg

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Fig. 11

Far-field sound pressure level spectra for M = 1.05 and EA 95 deg

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Fig. 12

Far-field sound pressure level spectra for M = 1.56 and EA 95 deg

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Fig. 13

Far-field sound pressure level spectra for M = 1.05 and EA 95 deg

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Fig. 14

Far-field sound pressure level spectra for M = 1.56 and EA 95 deg

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Fig. 15

Far-field sound pressure level spectra for M = 1.83 and EA 95 deg

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Fig. 16

Directivity of OASPL for different microphone polar angle M = 0.95

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Fig. 17

Directivity of OASPL for different microphone polar angle M = 1.05

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Fig. 18

Directivity of OASPL for different microphone polar angle M = 1.83

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Fig. 19

Directivity of OASPL for different microphone polar angle M = 1.05

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Fig. 20

Directivity of OASPL for different microphone polar angle M = 1.36

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Fig. 21

Directivity of OASPL for different microphone polar angle M = 1.83

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Fig. 22

Directivity of OASPL comparisons at M = 0.95

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Fig. 23

Directivity of OASPL comparisons at M = 1.83

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Fig. 24

Schlieren photographs at h/D = 2, M = 1.56 (left) and M = 1.83 (right) ((a) and (f): Nonswirl, (b) and (g): SFV0, (c) and (h): SCV20, (d) and (i): SCV40, and (e) and (j): SCV60)

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Fig. 25

Schlieren photographs at h/D = 5, M = 1.56 (left) and M = 1.83 (right) ((a) and (f): nonswirl, (b) and (g): SFV0, (c) and (h): SCV20, (d) and (i): SCV40, and (e) and (i): SCV60)

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