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동축 와류형 분사기의 연소안정성에 대한 분사기 리세스 및 연소실 길이의 영향
박수진(Sujin Bak),황동현(Donghyun Hwang),안규복(Kyubok Ahn),윤영빈(Youngbin Yoon) 한국추진공학회 2020 한국추진공학회지 Vol.24 No.1
In this study, model combustion tests were conducted to investigate the combustion instability characteristics of swirl coaxial injectors for a liquid rocket engine. To examine the effects of the combustion chamber resonant frequency and the injector mixing conditions, pressure fluctuations in the combustion chamber were measured by changing the combustion chamber length, injector recess length, and propellant mixture ratio. From the test results, the variation in the pressure fluctuations for each experimental condition was confirmed and the combustion stability was evaluated by stability mapping. It was found that the longitudinal mode and Kelvin-Helmholtz instabilities occurred due to the change in the combustion chamber and recess lengths.
기체메탄/기체산소 추진제를 이용한 동축 와류형 분사기에서의 예비 연소실험
황동현(Donghyun Hwang),박수진(Sujin Bak),안규복(Kyubok Ahn) 한국추진공학회 2019 한국추진공학회지 Vol.23 No.4
Combustion tests using six bi-swirl coaxial injectors with different shapes and recess lengths were performed in a model combustion chamber capable of flame visualization. By utilizing gaseous methane and gaseous oxygen instead of actual propellants, the effects of injector design and experimental conditions on the flame structure and combustion stability were analyzed. It was found that not only the experimental conditions but also the injector geometry such as the recess length and orifice diameter had a considerable influence on the combustion stability. In addition, it was confirmed that the heat release pattern changed with the occurrence of combustion instability.
황동현(Donghyun Hwang),박수진(Sujin Bak),안규복(Kyubok Ahn) 한국연소학회 2019 KOSCOSYMPOSIUM논문집 Vol.2019 No.11
An experimental study was conducted to investigate the effects of swirler geometry and flow condition on self-excited thermo-acoustic instability and bifurcation of flame structure. The combustion chamber length was manufactured in two types to simulate acoustically coupled/uncoupled conditions. Dynamic pressure, heat release, inlet velocity fluctuation, and CH* chemiluminescence image were measured to analyze the mechanism for combustion instability. Bifurcation of the flame structure was not necessarily coincide with the onset of thermo-acoustic instability, but occurred at nearly same condition regardless of the combustor length. The results showed that the combustion instability occurred based on the principle of the limit cycle in the case of coupled long combustor. In the uncoupled short combustor, however, only stable combustion was observed under the same flow conditions.