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The Effect of Turbine Blade Pitch on the Gas Turbine Engine Performance  

Kim, Jae-Min (부산대학교 항공우주공학과)
Kim, Kui-Soon (부산대학교 항공우주공학과)
Choi, Jeong-Yeol (부산대학교 항공우주공학과)
Jung, Yong-Wun (한국항공우주연구원 KHP 엔진팀)
Hwang, In-Hee (한국항공우주연구원 KHP 개발실)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.12, no.6, 2008 , pp. 48-55 More about this Journal
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.
Keywords
Engine Simulation; Turbine Geometry; Gas Turbine Engine; Computational Fluid Dynamics;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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