• Title/Summary/Keyword: 스퀼러 끝단

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Effect of Blade Tip Geometry on Heat Transfer Coefficients on Gas Turbine Blade Tips and Near Tip Regions (가스터빈 블레이드 끝단 형상에 따른 블레이드 끝단 및 그 주변에서의 열전달 계수 변화)

  • Kwak Jae-Su
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.30 no.4 s.247
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    • pp.328-336
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    • 2006
  • Detailed heat transfer coefficient distributions an two. types of gas turbine blade tip, plane tip and squealer tip, were measured using a hue-detection base transient liquid crystals technique.. The heat transfer coefficients an the shroud and near tip regions of the pressure and suction sides af the blade were also. measured. The heat transfer measurements were taken at the three different tip gap clearances af 1.0%, 1.5%, and 2.5% of blade span. Results shaw the overall heat transfer coefficients on the tip and shroud with squealer tip blade were lower than those with plane tip blade. By using squealer tip, however, the reductions af heat transfer coefficients near the tip regions of the pressure and suction sides were nat remarkable.

Numerical Investigation of Flow and Heat Transfer Characteristics on the Gas Turbine Blade with a Squealer Tip (스퀼러팁을 이용한 가스터빈 내에서의 3차원 유동 및 열전달 특성에 관한 연구)

  • Jung, Jong-Hun;Moon, Young-J.;Kim, Jin-Young
    • 한국전산유체공학회:학술대회논문집
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    • 2008.03b
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    • pp.159-162
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    • 2008
  • In this paper, a numerical simulation of three-dimensional flow field and heat transfer coefficient distribution are conducted for two types of gas turbine blade with plane and squealer tips. The numerical results show that gas turbine blade with squealer tip considerably changes the flow structures near the tip regions of pressure and suction sides, so the overall heat transfer coefficients on the tip and shroud with squealer tip are lower than those with the plane tip blade. Finally, the effect of tip gap clearance on the flow field and heat transfer characteristics are investigated.

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Numerical Analysis of Heat Transfer and Flow Characteristics on Squealer Tip of Gas Turbine Blade (가스터빈 블레이드 팁의 열전달과 유동 특성에 대한 수치적 해석)

  • Jiao, Liu;Kang, Youngseok;Kim, Donghwa;Cho, Jinsoo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.12
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    • pp.1062-1070
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    • 2016
  • The heat transfer and flow characteristics of gas turbine blade tip were investigated in this paper by using the conjugate heat transfer analysis. The rotor inlet boundary condition profile which was taken from the first stage nozzle outlet was used to analyse. The profile contained the velocity and temperature information. This study presents the influence of tip clearance about aerodynamic loss, heat transfer coefficient and film cooling effectiveness with the squealer tip designed blade model which tip clearance variation range from 1% to 2.5% of span. Results showed that the aerodynamic loss and the heat transfer coefficient were increased when the tip clearance was increased. Especially when the tip clearance was 2% of the span, the average heat transfer coefficient on the tip region was increased obviously. The film cooling effectiveness of tip region was increasing with decreasing of the tip clearance. There was high film cooling effectiveness at cavity and near tip hole region.