단계식 연소사이클 로켓엔진용 삼중분사 예연소기의 초임계 화염구조 해석
- Title
- 단계식 연소사이클 로켓엔진용 삼중분사 예연소기의 초임계 화염구조 해석
- Other Titles
- Modeling for Supercritical Flame Structure of Triplex Injection Preburner in Multi-Staged Rocket Combustion Cycle
- Author
- 김용모
- Keywords
- 로켓엔진; 예연소기; 초임계조건; 실유체효과; 화염편모델; Rocket engine; Preburner; Supercritical condition; Real fluid effect; Flamelet model
- Issue Date
- 2014-09
- Publisher
- 한국액체미립화학회
- Citation
- 한국액체미립화학회 학술발표논문집, 2014, 2014(0), P.17-18
- Abstract
- This study has been mainly motivated to numerically model the triplex injector preburner combustion which is operated in supercritical conditions encountered in rocket engine cycle. In the present approach, turbulence is represented by the standard k-e model. To account for the real fluid effects, the propellant mixture properties are calculated by using generalized cubic equation of state. In order to realistically represent the turbulence-chemistry interaction in the turbulent nonpremixed swirl flames, the flamelet approach based on the real fluid flamelet library has been adopted. Based on numerical results for triplex injector preburner, the detailed discussions are made for the effects of O/F ratio, pressure on Kerosene/LOx flame structure in supercritical conditions..
- URI
- http://kiss.kstudy.com/thesis/thesis-view.asp?key=3276241http://hdl.handle.net/20.500.11754/52649
- ISSN
- 1226-2277
- Appears in Collections:
- COLLEGE OF ENGINEERING[S](공과대학) > MECHANICAL ENGINEERING(기계공학부) > Articles
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