초록

본 연구를 통해 다상유동 수치모델링 기법 및 극저온 유체모델링을 기반으로 한 3차원 수치해석 프로그램을 개발하고, 이를 통해 액체로켓 터보펌프 인듀서의 흡입성능을 해석∙예측하였다. 이 과정에서 수행한 주요 연구 내용은 다음과 같이 요약할 수 있다.
1. 극저온 압축성 다상유동 수치해석 모델링 및 수치기법 정립
2. 극저온 유체 모델링 완성
3. 다상유동 수치해석 프로그램 개발 및 검증
4. 터보펌프 인듀서 해석
5. 흡입성능 향상을 위한 형상 설계 연구

Abstract ▼

Turbopump inducer is one of the key equipments determining the thrust capability of liquid rocket by pressurizing cryogenic oxidizer and fuel. In this process, instabilities due to cryogenic cavitation can lead to system malfunction or more seriously system failure, while physical understanding of t

Turbopump inducer is one of the key equipments determining the thrust capability of liquid rocket by pressurizing cryogenic oxidizer and fuel. In this process, instabilities due to cryogenic cavitation can lead to system malfunction or more seriously system failure, while physical understanding of this phenomena is quiet incomplete. In the present research, we have developed computational tools which can simulate and predict the cryogenic cavitating flows around turbopump inducer. This computational tools were extensively validated with various 2-D and 3-D problems including cavitating flows around a KARI turbopump inducer. Unsteady calculations were performed to describe the cavitation instabilities such as rotating cavitation and cavitation surge. Finally, we performed a shape design research to improved the suction performance of turbopump inducer.