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TECHNICAL PAPERS

Experimental Determination of Geometric Parameters for an Annular Injection Type Supersonic Ejector

[+] Author and Article Information
Sehoon Kim

3-Hynmoo-3, Agency for Defense Development, Jochiwongil 462, Yuseong, Daejeon, Republic of Korea

Sejin Kwon1

Division of Aerospace Engineering, Department of Mechanical Engineering,  Korea Advanced Institute of Science and Technology, 373-1 Guseong-dong, Yuseong-gu, Daejeon, 305-701, South Koreatrumpet@kaist.ac.kr

1

Corresponding author.

J. Fluids Eng 128(6), 1164-1171 (May 14, 2006) (8 pages) doi:10.1115/1.2353264 History: Received March 15, 2005; Revised May 14, 2006

The effects of four geometric parameters of an annular injection supersonic ejector, namely, the primary nozzle exit-to-throat area ratio, the contraction angle of the mixing chamber, the cross-sectional area and L/D ratio of the second-throat on the performance parameters including the secondary flow pressure, the starting pressure and unstarting pressure were investigated experimentally. The starting pressure exhibits linearly proportional dependence on the throat area ratio when the mixing chamber length is less than a certain critical value. For a longer mixing chamber, the starting pressure is proportional to the mixing chamber length while the unstarting pressure depends on the throat area ratio only. The geometric parameters of the second-throat do not affect the static pressure of the secondary flow. This implies that the secondary flow is aerodynamically choked in the mixing chamber and the static pressure of the secondary flow is determined by the choking condition since the mixing chamber of the annular injection ejector is relatively long. Based on the findings by the experiment, a simplified analytical model was proposed to predict the secondary flow pressure. The predicted secondary flow pressure agrees reasonably well with the measurement for a small contraction angle of the mixing chamber.

Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic of an annular injection type supersonic ejector with a second-throat

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Figure 2

A performance curve of a typical annular injection supersonic ejector with a second-throat

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Figure 3

Test installation of the annular injection supersonic ejector

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Figure 4

Effect of Mach number at primary nozzle exit

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Figure 5

Effect of mixing chamber contraction angle

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Figure 6

Effect of second-throat cross-sectional area

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Figure 7

Effect of second-throat L/D ratio

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Figure 8

Unstarting pressure with throat area ratio

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Figure 9

Starting pressure with mixing chamber length

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Figure 10

Diagram of stations and nomenclature used in the theoretical analysis

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Figure 11

Performance curves with various primary inlet Mach number

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Figure 12

Secondary flow pressure with entrainment ratio for primary inlet Mach number=4.0

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Figure 13

Compression ratio with entrainment ratio

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Figure 14

Secondary flow Mach number with entrainment ratio

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Figure 15

Distance to choking location with entrainment ratio

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