A Study on the Performance Evaluation of Dual Swirl Injectors

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Journal of the Korea Institute of Military Science and Technology 2003;6(4):113-123.

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Dual Swirl 인젝터의 성능 평가에 관한 연구

김선진, 정해승

¹청양대학 소방안전관리과
²충남대학교 기계공학과 대학원

Abstract

Both numerical analysis and experiment of cold and hot tests were performed to obtain basic design data for the swirl coaxial type Injector and to predict the combustion performance. Mass distribution, mixing distribution, mixing efficiency, characteristic velocity efficiency were measured by the cold tests and numerical analysis using the commercial thermo-hydraulic program. Test and analysis variables were recess, pressure drop, velocity ratio, mixing spray, mixture ratio. Hot tests were performed for the Uni-element injector to compare the performance with the cold test results, and, hot tests for Multi-element injector were performed to compare the performance with Uni-element injector. Designed thrust of the Uni-element injector liquid rocket was 35kgf at sea level and combustion chamber pressure, 20bar. Kerosene and Lox were used as a propellant.

Key Words: LRE(Liquid Rocket Engine), swirl injector