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Combustion Characteristics of Double Swirl Coaxial Injector in High Pressure Thrust Chamber  

서성현 (한국항공우주연구원 엔진그룹)
이광진 (한국항공우주연구원 엔진그룹)
한영민 (한국항공우주연구원 엔진그룹)
김승한 (한국항공우주연구원 엔진그룹)
김종규 (한국항공우주연구원 엔진그룹)
설우석 (한국항공우주연구원 엔진그룹)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.8, no.1, 2004 , pp. 54-60 More about this Journal
Abstract
Experimental study on combustion characteristics of double swirl coaxial injectors has been conducted for the assessment of critical injector design parameters. A reusable, subscale thrust chamber has been fabricated with a water-cooled copper nozzle. Two different configurations of injectors have been tested for the understanding of the effects of recess length on high pressure combustion. Clearly, the recess length drastically affects the combustion efficiency and hydraulic characteristics of an injector. Internal mixing of propellants in an injector with recess number of two increases a combustion efficiency and reveals sound combustion although a pressure drop required for the same amount of mass flow rates increases compared with an injector of recess number of one.
Keywords
Swirl Coaxial Injector; Recess Length; Reusable Thrust Chamber; Subscale Test;
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  • Reference
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