Browse

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

Cited 0 time in Web of Science Cited 0 time in Scopus
Authors
김형준; 민대호; 김종암
Issue Date
2013-02-28
Publisher
한국항공우주학회
Citation
제12회 우주발사체기술 심포지움, pp. 142-149
Keywords
공학Cryogenic cavitationTurbopump inducerTwo-phase flowAll-speed flow
Abstract
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.
Language
Korean
URI
https://hdl.handle.net/10371/83228
Files in This Item:
Appears in Collections:
College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Others_기계항공공학부
  • mendeley

Items in S-Space are protected by copyright, with all rights reserved, unless otherwise indicated.

Browse