한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제19권3호
  • /
  • Pages.29-38
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  • 2015
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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노즐-로터 축간극 거리에 따른 초음속 터빈 내의 성능특성에 대한 수치적 연구

A Numerical Study on a Supersonic Turbine Performance Characteristics with Different Nozzle-Rotor Axial Gap Spacings

  • Jeong, Sooin (Industrial Liaison Innovation Center, Pusan National University) ;
  • Choi, Byoung-ik (Rolls-Royce University Technology Center, Pusan National University) ;
  • Kim, Kuisoon (Department of Aerospace Engineering, Pusan National University)
  • 투고 : 2015.03.13
  • 심사 : 2015.05.14
  • 발행 : 2015.06.01
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초록

본 연구에서는 초음속 충동형 터빈의 노즐과 1단 로터 사이 축 간극 거리를 달리하며 3차원 비정상 유동해석을 수행하고 초음속 터빈의 성능 특성을 분석하였다. 계산결과는 기존의 초음속 터빈 효율 경향과 잘 일치하였으며 특정 축 간극 구간에서 효율의 급격한 감소를 보이고 그 이후에는 큰 변화가 없는 구간이 존재함을 확인하였다. 로터 앞전에서 발생하는 충격파의 영향이 노즐 끝단에 전달이 되는 정도에 따라 터빈 내의 여러 성능 특성이 달라짐을 살펴보았고 터빈 스팬 별 손실 특성에서 축 간극이 커질수록 허브 영역에서의 손실이 증가하고 미드스팬 이상의 영역에서 손실이 감소함을 보였다.

In this study, 3-dimensional URANS simulation was performed to analyze the effect of the nozzle-rotor axial gap spacing of a supersonic impulse turbine on turbine performance. The computations were conducted for four different axial gap cases corresponding to about 6%, 10%, 20% and 30% of the blade height, respectively. The results show a good agreement with previous studies and the turbine efficiency decreases drastically in certain range. It is examined that the turbine performance characteristics could change depending on the influence of leading edge shock to the nozzle outlet. It is also found that the entropy rise distributions along the span differ from each other.

키워드

참고문헌

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