Ignition and combustion characteristics of the gas turbine slinger combustor |
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Authors: | Seongman Choi Donghun Lee Jeongbae Park |
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Affiliation: | (1) Division of Mechanical and Aerospace System Engineering, Chonbuk National University, 664-14, Deokjin Dong 1 Ga, Jeonju City, Chonbuk, 561-756, Korea;(2) Power Systems R&D Center, Samsung Techwin Co. LTD., Sungju Dong 28, Changwon City, Gyeongnam, 641-717, Korea;(3) Agency for Defense Development, Yuseong, Daejeon, Korea |
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Abstract: | This paper describes the ignition and combustion characteristics of a gas turbine slinger combustor with rotating fuel injection
system. An ignition test was performed under various airflow, temperature and pressure conditions with fuel nozzle rotational
speed. From the test, there are two major factors influencing the ignition limits: the rotational speed of the fuel nozzle,
and the mass flow parameter. Better ignition capability could be attained through increasing the rotational speed and air
mass flow. From the spray visualization and drop size measurement, it was verified that there is a strong correlation between
ignition performance and drop size distribution. Also, we performed a combustion test to determine the effects of rotational
speed by measuring gas temperature and emission. The combustion efficiency was smoothly enhanced from 99% to 99.6% with increasing
rotational speed. The measured pattern factor was 15% and profile factor was 3%. |
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Keywords: | Slinger combustor Rotating fuel injection system Ignition Combustion |
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