Abstract
액체산소와 등유를 추진제로 사용하는 액체로켓엔진 터보펌프의 기본설계 사양을 도출하기 위한 1차원 시스템 설계 프로그램을 개발하였다. 터보펌프식 액체로켓엔진 시스템으로는 가스발생기 사이클과 단계식 연소 사이클 두 가지 사양을 고려하였다. 시스템 해석을 통하여 엔진 시스템의 유량 밸런스, 추력, 비추력, 혼합비, 터보펌프의 출력, 터빈 팽창비에 대한 분석이 수행되었으며 가스발생기를 제외한 대부분의 설계변수들이 실제 엔진과 잘 일치하는 결과를 얻었다. 본 논문에서는 개발된 1차원 시스템 설계 프로그램을 사용하여 임의의 액체로켓엔진 추력에 대한 터보펌프 기본 사양을 도출할 수 있음을 확인하였다. A 1-D system design program has been developed for the preliminary design of the turbopump system in liquid rocket engines, which use LOx and kerosene as propellants. Gasgenerator cycle and staged combustion cycle were considered as turbopump type liquid rocket engine systems. In the system analysis, mass flow balance, thrust, specific impulse, mixture ratios, turbopump power, and turbine expansion ratio of engine system were analyzed. Results show that most of the parameters agree well with real engine parameters except gasgenerator. Therefore, the l-D system design program developed in this study can be used to derive the preliminary design parameters of a turbopump with any thrust level liquid rocket engine.
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