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Ignition and combustion characteristics of the gas turbine slinger combustor

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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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Authors and Affiliations

  1. Division of Mechanical and Aerospace System Engineering, Chonbuk National University, 664-14, Deokjin Dong 1 Ga, Jeonju City, Chonbuk, 561-756, Korea

    Seongman Choi

  2. Power Systems R&D Center, Samsung Techwin Co. LTD., Sungju Dong 28, Changwon City, Gyeongnam, 641-717, Korea

    Donghun Lee

  3. Agency for Defense Development, Yuseong, Daejeon, Korea

    Jeongbae Park

Authors
  1. Seongman Choi
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  2. Donghun Lee
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  3. Jeongbae Park
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Correspondence to Seongman Choi.

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Choi, S., Lee, D. & Park, J. Ignition and combustion characteristics of the gas turbine slinger combustor. J Mech Sci Technol 22, 538–544 (2008). https://doi.org/10.1007/s12206-007-1106-6

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  • DOI: https://doi.org/10.1007/s12206-007-1106-6

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