Experimental Investigation of Cryogenic Line Chill-down Technology by Liquid Nitrogen

Cited 0 time in webofscience Cited 0 time in scopus
  • Hit : 252
  • Download : 586
Cryogenic propellants must be fed into rocket engines steadily in a subcooled state to avoid cavitation phenomena; therefore, the line chill-down process is significantly important in the cryogenic operation of space vehicles. Generally, some portion of the initially transported cryogenic liquids are used as the coolant to chill down the transfer line. Minimizing the line chill-down time and the consumption of the cryogenic propellant during the line chill-down is the main issue. In this study, the cryogenic line chill-down experiments are conducted on a 12.7 mm outer diameter, 1.25 mm wall thickness and 7 m long stainless steel horizontal pipe with liquid nitrogen (LN2). The pipe is vacuum jacketed to reduce heat inleak from room temperature environment to the cryogenic liquid. The temperature and the pressure profiles of the chill-down line are obtained at the location 6 meters away from the pipe inlet under various mass flow rates. The history of the transient temperature, the pressure and the mass flow rate are analyzed and presented for one representative pipe line geometry.
Publisher
한국항공우주학회
Issue Date
2016-08-11
Language
English
Citation

제16회 우주발사체기술 심포지움

URI
http://hdl.handle.net/10203/216527
Appears in Collection
ME-Conference Papers(학술회의논문)
Files in This Item
symposium2016_Jin Lingxue (최종).hwp(579 kB)Download

qr_code

  • mendeley

    citeulike


rss_1.0 rss_2.0 atom_1.0