Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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The Effect of Turbine Blade Pitch on the Gas Turbine Engine Performance

터빈의 피치 간격이 가스터빈 엔진 성능에 미치는 영향

  • 김재민 (부산대학교 항공우주공학과) ;
  • 김귀순 (부산대학교 항공우주공학과) ;
  • 최정열 (부산대학교 항공우주공학과) ;
  • 정용운 (한국항공우주연구원 KHP 엔진팀) ;
  • 황인희 (한국항공우주연구원 KHP 개발실)
  • Published : 2008.12.30
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Abstract

We have simulated the performance of a simple engine model with a gas turbine engine simulation program based on CFD. 2-dimensional Navier-Stokes code for the viscous flow was applied to simulate a compressor and a turbine, and the chemical equilibrium code with the lumped method was applied to simulate the combustor. Unsteady-flow phenomenon between rotor and stator of the compressor and the turbine was analyzed by steady mixing-plane method. In this way, the influence of the turbine blade pitch on the engine was investigated. It was shown that the compressor is operated at more higher pressure conditions as narrower the pitch distance of the turbine.

CFD 기반으로 개발한 가스터빈 엔진 모사 프로그램을 바탕으로 간단한 엔진 모델의 성능을 모사해보았다. 2D NS 코드를 사용하여 압축기와 터빈을 모사하고, lumped method 화학 평형 코드를 사용하여 연소기를 모사하였다. 압축기, 터빈에서의 동익, 정익간의 상호 비정상 유동 현상은 mixing-plane 기법으로 정상 상태 해석을 수행하였다. 이러한 방법으로 정상 작동 상태에서의 터빈 익렬의 피치 간격이 엔진에 미치는 영향을 살펴보았다. 연구 결과, 터빈의 피치 간격이 좁아질수록 압축기는 더 높은 압력에서 작동하는 것을 확인하였다.

Keywords

References

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