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지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
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연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 지도교수
- 고영성
- 발행연도
- 2016
- 저작권
- 충남대학교 논문은 저작권에 의해 보호받습니다.
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초록· 키워드
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An ultimate objective of this study is to measure the local heat flux of a liquid rocket engine combustion chamber using kerosene/liquid oxygen. The heat flux was measured experimentally by Advanced Integral Method at mixture ratio 2.2 and chamber pressure 9.5 bar. The conclusions for the measurement method of the heat flux gauge and the result of experiment were as follows.
1) Advanced Integral Method is necessary for solving the problem that the heat flux by Original Integral Method was significantly different with the actual heat flux.
2) As a result of the calibration test on the fabricated heat flux gauge according to the intensity of fiber laser irradiation, it is confirmed that the measured value of heat flux were approximately 7.5∼8 percent below the actual heat flux.
3) When the hot test was performed using the heat flux gage, it is possible to understand the thermal behavior over time in the localized area of the combustion chamber.
4) The heat flux in the steady state was measured as 1.8∼1.9 and it was judged to be appropriate as compared to the reference data.
5) The heat transfer coefficient could be calculated through convective heat transfer equation based on results of CEA code and the heat flux of Advanced Integral Method. The value of steady state was calculated as 740∼760.
Through this study, it was organized to re-establish the measurement method of the plug-type heat flux gauge and the heat flux of the rocket combustion chamber for the design of the combustion chamber of the cooling device was measured and analyzed. This results of this study is expected to be used for basic data to design and fabricate the heat flux gauge suitable for domestic rocket and the measurement method of heat flux.
1) Advanced Integral Method is necessary for solving the problem that the heat flux by Original Integral Method was significantly different with the actual heat flux.
2) As a result of the calibration test on the fabricated heat flux gauge according to the intensity of fiber laser irradiation, it is confirmed that the measured value of heat flux were approximately 7.5∼8 percent below the actual heat flux.
3) When the hot test was performed using the heat flux gage, it is possible to understand the thermal behavior over time in the localized area of the combustion chamber.
4) The heat flux in the steady state was measured as 1.8∼1.9 and it was judged to be appropriate as compared to the reference data.
5) The heat transfer coefficient could be calculated through convective heat transfer equation based on results of CEA code and the heat flux of Advanced Integral Method. The value of steady state was calculated as 740∼760.
Through this study, it was organized to re-establish the measurement method of the plug-type heat flux gauge and the heat flux of the rocket combustion chamber for the design of the combustion chamber of the cooling device was measured and analyzed. This results of this study is expected to be used for basic data to design and fabricate the heat flux gauge suitable for domestic rocket and the measurement method of heat flux.
목차
1.1 교정 시험 개략도 351.2 Black Paint 361.3 Fiber Laser 372. 교정 시험 방법 393. 데이터 처리 방법 413.1 수치해석 조건 413.2 가우시안 빔(Gaussian beam) 424. 교정 시험 결과 43V. 실험 장치 및 방법 481. 연소 실험 장치 482. 연소 실험 방법 53Ⅵ. 실험 결과 및 고찰 551. 연소 실험 및 온도 측정 결과 552. 열유속 결과 및 분석 573. 대류 열전달 계수 결과 및 분석 62Ⅶ. 결론 64참고문헌 66ABSTRACT 70
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