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


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
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Figure 1

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

Grahic Jump Location
Figure 2

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

Grahic Jump Location
Figure 3

Test installation of the annular injection supersonic ejector

Grahic Jump Location
Figure 4

Effect of Mach number at primary nozzle exit

Grahic Jump Location
Figure 5

Effect of mixing chamber contraction angle

Grahic Jump Location
Figure 6

Effect of second-throat cross-sectional area

Grahic Jump Location
Figure 7

Effect of second-throat L/D ratio

Grahic Jump Location
Figure 8

Unstarting pressure with throat area ratio

Grahic Jump Location
Figure 9

Starting pressure with mixing chamber length

Grahic Jump Location
Figure 10

Diagram of stations and nomenclature used in the theoretical analysis

Grahic Jump Location
Figure 11

Performance curves with various primary inlet Mach number

Grahic Jump Location
Figure 12

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

Grahic Jump Location
Figure 13

Compression ratio with entrainment ratio

Grahic Jump Location
Figure 14

Secondary flow Mach number with entrainment ratio

Grahic Jump Location
Figure 15

Distance to choking location with entrainment ratio



Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In