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Research Papers

Computational Investigation of Cold Flow in a Dump Combustor With Tapered Exit

[+] Author and Article Information
R. Sailaja

Department of Aerospace Engineering, Indian Institute of Technology Kanpur, Kanpur 208016, Indiasailu@iitk.ac.in

N. P. Yadav

Department of Aerospace Engineering, Indian Institute of Technology Kanpur, Kanpur 208016, Indianagendra@iitk.ac.in

A. Kushari

Department of Aerospace Engineering, Indian Institute of Technology Kanpur, Kanpur 208016, Indiaakushari@iitk.ac.in

J. Thermal Sci. Eng. Appl 2(1), 011009 (Sep 24, 2010) (7 pages) doi:10.1115/1.4002426 History: Received February 19, 2010; Revised August 11, 2010; Published September 24, 2010; Online September 24, 2010

This paper reports the results of a numerical study of the cold flow field in a dump combustor with a tapered exit. The numerical model was benchmarked against the data available in the literature. The flow field inside the combustor was investigated by numerical visualization of different regions in the flow field, and the effect of the combustor length was studied. It was seen that the presence of shear layer between the potential core and the recirculation region, as well as the pressure and velocity variation inside the combustor, alters the recirculation region and hence the flow field. It was also observed that the extent of the recirculation region increases, while the shear layer becomes thinner as the length of the chamber decreases. The effect of the variation in the flow Reynolds number and the inlet turbulence intensity on the flow field of a low aspect ratio (2.3) dump combustor was studied in detail. It was observed that the extent of recirculating flow increases with a decrease in the Reynolds number, and the increase in turbulence intensity results in higher turbulence energy generation in the shear layer. The pressure recovery was found less, but the recirculation was stronger in the low aspect ratio combustor. The results of this study can help optimize the combustor chamber to achieve better mixing of fuel with air and stabilization of the flame.

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Copyright © 2010 by American Institute of Physics
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Figures

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Figure 1

Schematic representation of the flow field in the dump combustor

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Figure 2

Grid pattern of the geometry

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Figure 3

Grid independence test results at Re=1.26×105 and z/H=0.74

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Figure 4

(a) Variation in pressure drop with expansion ratio at Re=7.5×104 and LC/DC=10. (b) Variation in pressure drop with chamber length-to-diameter ratio at Re=7.5×104 and DN/DC=0.2.

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Figure 5

(a) Radial distribution of normalized axial velocity component in sudden expansion geometry at Re=1.26×105 and I=1%. (b) Radial distribution of normalized radial velocity component in sudden expansion geometry at Re=1.26×105 and I=1%.

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Figure 6

Axial velocity field for different chamber lengths; expansion ratio=0.265 at Re=1.26×105 and I=1%

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Figure 7

Variation in centerline velocity with the axial distance for different chamber lengths (LC) and an expansion ratio of 0.265 at Re=1.26×105 and turbulent intensity I=1%

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Figure 8

Radial distribution of normalized axial velocity component for different combustor lengths for an expansion ratio of 0.265 at Re=1.26×105 and I=1%: (a) x/h=5, (b) x/h=8, and (c) x/h=10.5

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Figure 9

Radial distribution of the radial velocity component of different chamber lengths for an expansion ratio of 0.265 at Re=1.26×105 and I=1%: (a) x/h=5, (b) x/h=8, and (c) x/h=10.5

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Figure 10

Wall pressure distribution for different chamber lengths (LC) and an expansion ratio of 0.265 at Re=1.26×105 and turbulent intensity I=1%

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Figure 11

Velocity field inside a low aspect ratio dump combustor at Re=1.26×105 and I=5%: (a) axial velocity and (b) radial velocity

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Figure 12

Axial variation in normalized centerline velocity for a low aspect ratio combustor at Re=1.26×105 and I=5%

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Figure 13

Radial variation in velocity components and kinetic energy for three different Reynolds numbers at x=10.5 h after the dump plane in a low aspect ratio combustor of expansion ratio of 0.265 at 1% turbulence intensity. (a) Axial velocity, (b) radial velocity, and (c) kinetic energy.

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Figure 14

Radial distribution of (a) radial velocity component and (b) kinetic energy for three different turbulence intensities at x=10.5 h after the dump plane in a low aspect ratio combustor of expansion ratio of 0.265 at Re=1.26×105

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