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http://dx.doi.org/10.5139/JKSAS.2003.31.10.060

A Study of Ignition Performance on the Annular Combustor with Rotating Fuel Injection System  

Lee, Gang-Yeop (삼성테크윈(주) 파워시스템 연구소)
Lee, Dong-Hun (삼성테크윈(주) 파워시스템 연구소)
Choe, Seong-Man (삼성테크윈(주) 파워시스템 연구소)
Park, Jeong-Bae (국방과학연구소)
Kim, Hyeong-Mo (한국항공우주연구원)
Park, Yeong-Il (한국항공우주연구원)
Go, Yeong-Seong (한국항공우주연구원)
Han, Yeong-Min (한국항공우주연구원)
Yang, Su-Seok (한국항공우주연구원)
Lee, Su-Yong (한국항공우주연구원)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.31, no.10, 2003 , pp. 60-65 More about this Journal
Abstract
An experimental study was performed to understand ignition characteristics of gas turbine combustor with rotating fuel injection system. Liquid fuel applied to the inner surface of rotating fuel nozzle which was driven by high speed electrical motor is flung away by centrifugal forces. The real scale combustor and test rig was manufactured and tested under atmospheric condition in KARl combustion test facility. From the test results, this combustor ignition characteristics are highly dependent upon fuel nozzle rotating speed. Futhermore, combustor exit gas temperature was rapidly changed by increasing or decreasing the fuel nozzle rotating speed.
Keywords
Gas Turbine; Spray; Annular Combustor; Rotating Fuel Injection System; Ignition;
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  • Reference
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