Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : September 05, 2021 - September 08, 2021
The rocket engine combustion instability was investigated. The pressures increased by combustion were different in the previous two tests. Pressures were 1.5 to 3 times higher than that before combustion in 2019 model. In another 2020 model, pressures were 1.1 to 17 times higher. In the present study, the equivalence ratio in the two models was measured. Fuel was 2-propanol, and oxidizer was oxygen gas. Mixture was sampled from the combustor models. According to the sampled gas, the equivalence ratio was approximately 0.7 in 2019 model. In 2020 model, the ratio was approximately 1. According to mixture temperature in the combustor model, mixture was vapor in 2019 model, and was mist in 2020 model. The large equivalence ratio and large pressure increase will have relation to the mixture condition.
