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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

# Liquid Jets in Subsonic Air Crossflow at Elevated Pressure

[+] Author and Article Information
Jinkwan Song

Combustion Research Laboratory,
School of Aerospace Systems,
University of Cincinnati,
745 Baldwin Hall,
Cincinnati, OH 45221-0070
e-mail: jinkwasg@uc.edu

Charles Cary Cain

Combustion Research Laboratory,
School of Aerospace Systems,
University of Cincinnati,
745 Baldwin Hall,
Cincinnati, OH 45221-0070
e-mail: cccain@gmail.com

Jong Guen Lee

Mem. ASME
Combustion Research Laboratory,
School of Aerospace Systems,
University of Cincinnati,
745 Baldwin Hall,
Cincinnati, OH 45221-0070
e-mail: Jongguen.lee@uc.edu

1Corresponding author.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 10, 2014; final manuscript received July 24, 2014; published online October 28, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(4), 041502 (Oct 28, 2014) (12 pages) Paper No: GTP-14-1369; doi: 10.1115/1.4028565 History: Received July 10, 2014; Revised July 24, 2014

## Abstract

The breakup, penetration, droplet size, and size distribution of a Jet A-1 fuel in air crossflow has been investigated with focus given to the impact of surrounding air pressure. Data have been collected by particle Doppler phased analyzer (PDPA), Mie-scattering with high speed photography augmented by laser sheet, and Mie-scattering with intensified charge-coupled device (ICCD) camera augmented by nanopulse lamp. Nozzle orifice diameter, do, was 0.508 mm and nozzle orifice length to diameter ratio, lo/do, was 5.5. Air crossflow velocities ranged from 29.57 to 137.15 m/s, air pressures from 2.07 to 9.65 bar, and temperature held constant at 294.26 K. Fuel flow provides a range of fuel/air momentum flux ratio (q) from 5 to 25 and Weber number from 250 to 1000. From the results, adjusted correlation of the mean drop size has been proposed using drop size data measured by PDPA as follows: $(D0/D32)=0.267Wea0.44q0.08(ρl/ρa)0.30(μl/μa)-0.16$. This correlation agrees well and shows roles of aerodynamic Weber number, Wea, momentum flux ratio, q, and density ratio, ρl/ρa. Change of the breakup regime map with respect to surrounding air pressure has been observed and revealed that the boundary between each breakup modes can be predicted by a transformed correlation obtained from above correlation. In addition, the spray trajectory for the maximum Mie-scattering intensity at each axial location downstream of injector is extracted from averaged Mie-scattering images. From these results, correlations with the relevant parameters including q, x/do, density ratio, viscosity ratio, and Weber number are made over a range of conditions. According to spray trajectory at the maximum Mie-scattering intensity, the effect of surrounding air pressure becomes more important in the farfield. On the other hand, effect of aerodynamic Weber number is more important in the nearfield.

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## Figures

Fig. 1

High pressure chamber geometries

Fig. 2

Test section geometry and diagnostic equipment focuses

Fig. 3

Injector geometry

Fig. 4

The comparison between present data measured by PDPA and the correlation suggested by Ingebo [14]

Fig. 5

The adjusted correlation of the mean drop size in terms of Wea, q, ρl/ρa, and μl/μa

Fig. 6

The effect of the surrounding air pressure on the drop size distribution; (a) Wea = 500, q = 10 and (b) Wea = 1000, q = 10

Fig. 7

The effects of the aerodynamic Weber number and momentum flux ratio on the drop size distribution; (a) Pa = 2.07 bar, q = 10 and (b) Wea = 250

Fig. 8

Changes of the several different forms for mean drop size with respect to change of surrounding air pressure

Fig. 9

The relation between D32 and D63.2%

Fig. 10

Instantaneous images at each surrounding air pressure with aerodynamic Weber number of 500 and q of 10; (a) Pa = 2.07 bar (transition), (b) Pa = 3.45 bar (transition), (c) Pa = 6.89 bar (transition), and (d) Pa = 9.65 bar (transition)

Fig. 11

Instantaneous images at each surrounding air pressure with surrounding air pressure of 6.89 bar and q of 10; (a) Wea = 250 (multimode), (b) Wea = 750 (transition), and (c) Wea = 1000 (shear)

Fig. 12

Jet breakup regime map at each surrounding air pressure; (a) Pa = 2.07 bar, (b) Pa = 3.45 bar, (c) Pa = 6.89 bar, and (d) Pa = 9.65 bar

Fig. 13

The trajectory correlations of spray for the maximum Mie-scattering intensity

Fig. 14

Nearfield correlation change with respect to aerodynamic Weber number change

Fig. 15

Farfield correlation change with respect to aerodynamic Weber number change

Fig. 16

Nearfield correlation change with respect to surrounding air pressure change

Fig. 17

Farfield correlation change with respect to surrounding air pressure change

Fig. 18

Comparison between volume flux measured by PDPA and Mie-scattering intensity taken by high speed camera; (a) volume flux and valid rate in Wea = 250 and 1000 and (b) corrected volume flux and Mie-scattering intensity profile

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