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A Study on the Performance Evaluation of Dual Swirl Injectors  

김선진 (청양대학 소방안전관리과)
정해승 (충남대학교 기계공학과 대학원)
Publication Information
Journal of the Korea Institute of Military Science and Technology / v.6, no.4, 2003 , pp. 113-123 More about this Journal
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.
Keywords
LRE(Liquid Rocket Engine); swirl injector;
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  • Reference
1 D. P. Sclunidt, I. Nouar, P. K Senecal, C. J. Rutland, J. K Martin and R. D. Reitz, 'Pressure Swirl Atomization in the Near Field', SAE Paper 01-0496, SAE, 1996
2 Hiroshi Tamura, etc, 'Injection and Combustion Characteristics of Unlike Impinging Triplet Injector for LOX-Kerosene Rocket Combustor', NAL TR 648, 1980
3 N. K ,Rizk and A. H. Lefebvre, 'Prediction of velocity coefficient and spray cone angle for simplex swirl atomizers', ICLASS-85
4 Martin Hersch, 'A Mixing model for rocket engine combustion', NASA TN D-2881, 1965
5 Kazuo SATO , 'A Study of N204/Amine Injector Elements Part 1 Cold Flow Test', 航空宇宙技術報告 TR-899, pp.1-13, 1986. 2