Ignition Performance of Double Vortex Combustor
Mach number of interstage turbine combustor is between 0.25 and 0. 6, which is higher than main combustor. Because of the high velocity of mainstream, the organization of combustion is difficult and the boundary of stable combustion is narrow if the conventional swirl combustor scheme is adopted The structure of trapped vortex combustor (TVC) is different from swirl combustor, and the combustion zone of TVC is located in the cavity zone. Because stable recirculation zone can be established in the cavity zone, wide operating range of combustor could be acquired under the conditions of high velocity of inlet. The ignition performance of a double vortex combustor is investigated by experimental approaches. Aviation kerosene is chosen as the fuel of combustor, and three evaporation tubes are used as oil supply equipment, and the high-energy spark plug is used as ignition equipment. The effect of temperature of mainstream, Mach number of mainstream, ignition energy, and position of spark plug on the ignition performance is investigated. The results of the ignition experiment show thatdouble vortex combustor has a wide range of ignition, and the increase of ignition energy is beneficial to the improvement of ignition performance. When the Mach number and inlet temperature of combustor change, there is a large difference in ignition performance between different ignition positions.
ignition performance vortex combustor interstage turbine combustor evaporation tube
Zhang Rongchun Fan Weijun Zhang Tao
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191, China School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
1176-1179
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）