Study on the Ignition Characteristics of Liquid Rocket Engine Combustor and Gas Generator
액체로켓엔진 연소기 및 가스발생기의 점화 특성 연구
-
Kim, Seung-Han
;
-
Moon, Il-Yoon
;
-
Lee, Kwang-Jin
;
-
Kim, Jong-Kyu
;
- Seo, Seong-Hyun ;
-
Kim, Seong-Ku
;
-
Seol, Woo-Seok
-
김승한
(한국항공우주연구원 우주추진기관실 엔진그룹)
;
-
문일윤
(한국항공우주연구원 우주추진기관실 엔진그룹)
;
-
이광진
(한국항공우주연구원 우주추진기관실 엔진그룹)
;
-
김종규
(한국항공우주연구원 우주추진기관실 엔진그룹)
;
- 서성현 (한국항공우주연구원 우주추진기관실 엔진그룹) ;
-
김성구
(한국항공우주연구원 우주추진기관실 엔진그룹)
;
-
설우석
(한국항공우주연구원 우주추진기관실 엔진그룹)
- Published : 2003.12.12
Abstract
Study on the ignition characteristics of combustor and gas generator for LOx-kerosene liquid rocket engine was performed experimentally through a series of combustion tests of sub-scale engine combustor and gas generator. Characteristic of gas-torch ignitor based on gaseous methane and gaseous oxygen was compared with hypergolic ignition using propellant tri-ethyl-aluminium. Gas-torch ignitor showed good performance on igniting sub-scale liquid rocket engine combustor and gas generator. It was observed that the ignition delay is also affected by the extent of nitrogen in the combustion chamber.
Keywords