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Flow Coefficient Experiments of a Hypergolic Igniter with Rupture Disc Ends  

Yoo, Jaehan (한국항공우주연구원 미래로켓연구팀)
Lee, Joongyoup (한국항공우주연구원 미래로켓연구팀)
Lee, Soo Yong (한국항공우주연구원 미래로켓연구팀)
Publication Information
Aerospace Engineering and Technology / v.11, no.2, 2012 , pp. 122-128 More about this Journal
Abstract
Many of the liquid rocket engines use a hypergolic igniter with rupture disc ends located in the combustion chamber ignition line. In this study, the flow coefficient tests of the igniter, which have a solenoid valve upstream, were performed. The tension-type rupture discs for radial and circumferential scores and the igniter with them were tested using water at room temperature. The effects of the score, flow rate, the disc thickness, gas pocket and the solenoid valve on the coefficient were analyzed.
Keywords
Liquid Rocket Engine; Hypergolic Igniter; Rupture Disc; Score; Tension-type; Flow Coefficient; Test;
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  • Reference
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