S-Space College of Engineering/Engineering Practice School (공과대학/대학원) Dept. of Mechanical Aerospace Engineering (기계항공공학부) Others_기계항공공학부
극저온 이상유동 고정밀 수치해석을 통한 액체로켓 터보펌프 인듀서 성능예측 연구
Performance Prediction of Liquid Rocket Turbo-pump Inducer using a high fidelity cryogenic two-phase computation
- 김형준; 민대호; 김종암
- Issue Date
- 제12회 우주발사체기술 심포지움, pp. 142-149
- The present paper deals with a numerical simulation of cryogenic cavitating flows around turbopump inducer in liquid rocket. Recently, we have developed an accurate and efficient baseline numerical scheme for the computations of all-speed two-phase flows. Firstly, by extending such progress, we conduct some modification of preconditioning technique and propose an accurate and efficient numerical method to deal with the computations of cryogenic two-phase flows. Secondly, we compute and compare, for the purpose of validating the proposed method, two-dimensional/axis-symmetric cryogenic cavitation flows around hydrofoil and ogive. Finally, numerical simulations of three-dimensional KARI turbopump inducer are carried out under various flow conditions with water and cryogenic fluids, and we examine the differences in inducer flow physics depending on the working fluids.