Improvement of the Startup Transient Analysis on the Liquid Rocket Engine Using the TP+GG Coupled Test Result

터보펌프+가스발생기 연계시험 결과를 이용한 액체로켓엔진 시동 과정에 대한 해석 방법의 개선

The turbopump+gas generator (TP+GG) coupled test for the liquid rocket engine development was performed. By comparing the results of a engine startup transient analysis with this test results, the verification of the analysis model was performed. From this, as to the analysis of the engine startup, the method calculating the pressure ratio of the turbine during the initial stage of startup was improved. And a fact that the transient heat transfer phenomenon between the working fluid and the solid parts of turbine effects to the calculation of turbine pressure ratio and consequentially to the startup analysis was revealed.

액체로켓 엔진의 개발을 위한 터보펌프+가스발생기(TP+GG) 연계시험을 수행하였으며, 본 시험결과와 Flowmaster를 이용한 엔진 시동해석 결과를 비교함으로써 시동해석 방법의 검증을 수행하였다. 이로부터 엔진 시동해석에 있어서, 초기 터빈의 압력비를 계산하는 방법을 개선하였으며, 특히 시동 초기의 터빈 출구 온도가 시동 해석의 오차에 미치는 영향을 확인하였다.