액체로켓엔진 고고도 모사용 2차목 초음속 디퓨져 설계변수에 따른 특성 고찰

Investigation of Characteristics of Second Throat Exhaust Diffuser for Simulating High-Altitude of Liquid Rocket Engine According to Design Parameter

2차목 초음속 디퓨져 입구 직경에 따른 진공실 압력 변화를 고찰하였다. 디퓨져 입구는 세 종류로 변화시켰으며 각각의 경우에 대해 전산유체역학을 통해 계산을 수행하였다. 디퓨져 입구 크기에 따른 진공실의 압력 변화를 빠르게 상대비교하기 위해 비점성으로 가정한 Euler 방정식을 지배방정식으로 채택하였다. 결과로부터 디퓨져의 입구크기가 증가하면 진공실의 압력은 감소하는 것을 관찰할 수 있었다.

The vacuum chamber pressure was investigated according to the second throat exhaust diffuser entrance diameter. The sizes of diffuser entrance were changed three cases, and each case was computed by using CFD. Also in order to relatively compare the vacuum chamber pressure the Euler equation was adopted. According to the results, as the size of diffuser entrance was increased it was observed that the vacuum chamber pressure was decreased.