Prediction of Turbulent Jet Mixing Noise Reduction by Water Injection Max Kandula' ASRC Aerospace, NASA Kennedy Space Center, Florida 32899, USA A one-dimensional control volume formulation is developed for the determination of jet mixing noise reduction due to water injection. The analysis starts from the conservation of mass, momentum and energy for the confrol volume, and introduces the concept of effective jet parameters (jet temperature, jet velocity and jet Mach number). It is shown that the water to jet mass flow rate ratio is an important parameter characterizing the jet noise reduction on account of gas-to-droplet momentum and heat transfer. Two independent dimensionless invariant groups are postulated, and provide the necessary relations for the droplet size and droplet Reynolds number. Results are presented illustrating the effect of mass flow rate ratio on the jet mixing noise reduction for a range of jet Mach number and jet Reynolds number. Predictions from the model show satisfactory comparison with available test data on perfectly expanded hot supersonic jets. The results suggest that significant noise reductions can be achieved at increased flow rate ratios. 'Subject Matter Expert, Mailstop ASRC-52 11, Associate Fellow AIAA. https://ntrs.nasa.gov/search.jsp?R=20130011511 2018-07-17T13:13:20+00:00Z
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Prediction of Turbulent Jet Mixing Noise Reduction by
Water Injection
Max Kandula'
ASRC Aerospace, NASA Kennedy Space Center, Florida 32899, USA
A one-dimensional control volume formulation is developed for the determination of jet
mixing noise reduction due to water injection. The analysis starts from the conservation of
mass, momentum and energy for the confrol volume, and introduces the concept of effective
jet parameters (jet temperature, jet velocity and jet Mach number). It is shown that the
water to jet mass flow rate ratio is an important parameter characterizing the jet noise
reduction on account of gas-to-droplet momentum and heat transfer. Two independent
dimensionless invariant groups are postulated, and provide the necessary relations for the
droplet size and droplet Reynolds number. Results are presented illustrating the effect of
mass flow rate ratio on the jet mixing noise reduction for a range of jet Mach number and
jet Reynolds number. Predictions from the model show satisfactory comparison with
available test data on perfectly expanded hot supersonic jets. The results suggest that
significant noise reductions can be achieved at increased flow rate ratios.
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Aeroacoustics Conference, Manchester, Great Britain, May 2004.
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[101 Washington, D., and Krothapalli, A., The role of water injection on the mixing noise of supersonic jet, AIAA
Paper 98-2205, June 1998.
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reduction by water injection, AIAA-2007-3645, 2007.
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24
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[44] Kandula, M., Spectral attenuation of sound in dilute suspensions with nonlinear particle relaxation, accepted
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26
Captions to Figures
Fig. 1 Schematic of the jet configuration with water injection.
Fig. 2. Effect ofjet Mach number and jet temperature on overall sound power, from Kandula [34].
Fig. 3a Variation of the fractional evaporation with the jet Reynolds number.
Fig. 3b Variation of fractional evaporation with jet temperature.
Fig. 4a Variation of effective jet velocity with the water mass flow rate.
Fig. 4b Variation of effective jet temperature with the water mass flow rate.
Fig. 4c Variation of effective jet Mach number with the water mass flow rate.
Fig. 4d Variation of effective jet density with the water mass flow rate.
Fig. 4e Variation of effective jet cross sectional area with the water mass flow rate.
Fig. 5a Dependence of effective jet velocity with jet Reynolds number.
Fig. 5b Dependence of effective jet temperature on jet Reynolds number.
Fig. 5c Dependence of effective jet Mach number on jet Reynolds number.
Fig. 6 Comparison of the predictions with data of Norum (2004) for turbulent mixing noise reduction due to water injection.
27
nozzle exit plane
water _-injection
0
0...
L_ 2
potential core
shear layer
Fig. 1 Schematic of the jet configuration with water injection.
-60 .-• - --ItT =4.0 p in!
-800.1 I 10
Jet Mach number, M.
Fig. 2. Effect ofjet Mach number and jet temperature on overall sound power, from Kandula [34].
28
0.7 —T=833K
p1 p1 = 3800 -T=1389
0.6- T1=1944k
0.2
10' 106 10
Re. J
Fig. 3a Variation of the fractional evaporation with the jet Reynolds number.
0.2 // Re = 10', p/p = 3800 -
0.1 / i--i
0
400 600 800 1000 1200 1400 1600 1800
T.,k Fig. 3b Variation of fractional evaporation with jet temperature.
29
0.9
- 0.8
e.l =• 0.7
0.6
0.50 2 8 ID
Fig. 4a Variation of effective jet velocity with the water mass flow rate.
- 0.8 - - - - - - - - -
— M =O.l7 p
Re10
M1=I.0j ii
M =2.01 ii
0.6 --M=.3.j
0.50 2 8 10
Fig. 4b Variation of effective jet temperature with the water mass flow rate.
30
0.6--M11=J.5
0.50 2 8 10
Fig. 4c Variation of effective jet Mach number with the water mass flow rate.
1.6
1.5
1.4
P12'P1
— M =0.1 ii
rsl =1.0 ii
--rs1 =2.0 ii
ThT
Re =10 ii
1 TS1 =3.5
L ji
1.2
1 .1 .-.-.-.-.-.-.-.-.---.-.---.-.-.- -
th/rh1 Fig. 4d Variation of effective jet density with the water mass flow rate.
31
10
__________ Re = i07
0 2
thw1thji Fig. 4e Variation of effective jet cross sectional area with the water mass flow rate.
— Re 1.OE5
0.9
0.50 2 4 8 10
Fig. 5a Dependence of effective jet velocity with jet Reynolds number.
32
—Re I.0E5 ii
Re=I.0E6
0.6 --Re=l.0E7
--Re =I.0E8 ii
0.50 2 4 6 8 10
th/th Fig. 5b Dependence of effective jet temperature on jet Reynolds number.
'.. 0.7 —Re = 1.0E5 _____________
--- - ReI.0E6 I
0.6 Re = 1.0E7 ii
"Re 1.0E8 0.5
0 2 4 6 8 10
mw/mjl
Fig. Sc Dependence of effective jet Mach number on jet Reynolds number.
33
Perfectis EpantIcd hot supersonic jet mixing noise (case C)
(ID
03
6- present theory
• data (Nortini 2004; 45 deg inj. angle)
0 0.2 0.4 0.6 0.8 1
th/th Fig. 6 Comparison of the predictions with data of Norum (2004) for turbulent mixing noise reduction due to water injection.
34
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ASRC-521 1 Kennedy Space Center, FL 32899
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14. ABSTRACT A one-dimensional control volume formulation is developed for the determination ofjet mixing noise reduction due to water injection. The analysis starts from the conservation of mass, momentum and energy for the control volume, and introduces the concept of effective jet parameters (jet temperaturem jet vlocity, and jet Mach number). It is shown that the water to jet mass flow ratio is an important parameter characterizing the jet noise reduction on account of gas-to-droplet momentum and heat transfer, Two independent dimensionless invariant groups are postulated, and provide the necessary relations for the droplet size and droplet Reynolds number. Results are presented illustrating the effect of mass flow rate ratio on the jet mixing noise reduction for a range of jet Mach mumber and jet Reynolds number. Predictions from the model show satisfactory comparison with available test data on perfectly expanded hot supersonic jets. The results suggest that significant noise reductions can be achieved at increased flow rates.
15. SUBJECT TERMS spectral attenuation
16. SECURITY CLASSIFICATION OF: 17. LIMITATION OF 18. NUMBER
PAGES
19b. NAME OF RESPONSIBLE PERSON
Max Kandula a. REPORT b. ABSTRACT c. THIS PAGE19b. TELEPHONE NUMBER (Include area code)
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