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나상권(S.K. Na),심재경(J.K. Shim),박희호(H.H. Park),이성준(S.J. Lee),전승배(S.B. Chen) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
It is very difficult to understand and estimate the heat transfer and flow characteristics in the combustor, which is one of main components in the Auxiliary Power Unit (APU), because its flow filed has very complex structure. In this paper, specified is characteristics of injection and flow through different air holes in the liner, which consist of large circular holes, film cooling holes, and tangential air swirl holes. The durability of the liner depends on whether the surface of the liner is exposed to the hot gas over 1000℃ of a temperature or not. It is proved that the locations of hot spots estimated from the calculation using CFD are matched well with that from the test. In this study, CFD simulations were performed to examine the heat transfer and temperature distributions in and about a liner wall with film cooling on the wall. This computational study is based on the ensemble average continuity, compressible Navier-Stokes, energy, and PDF combustion equations closed by the standard k-ε turbulence model with standard wall functions for the gas phase and the Fourier equations for conduction in the solid phase.
최재호(J. H. Choi),이진수(J. S. Lee),조현준(H. J. Cho),이성준(S. J. Lee),전승배(S. B. Chen),차봉준(B. J. Cha) 한국유체기계학회 2008 유체기계 연구개발 발표회 논문집 Vol.2008 No.-
This paper presents an aerodynamic design, flow analysis and performance test of a transonic centrifugal compressor for APU applications. The compressor is made up of a centrifugal impeller, a wedge diffuser and a des wirier. The impeller and diffuser for this kind of application should be developed to meet air-bleeding requirement and shaft power extraction requirements, that is, very wide operational range. Aerodynamic design for this purpose is performed and three-dimensional numerical analysis with Reynolds-averaged Navier-Stokes solver is performed to analyze the flows in the impeller, diffuser and deswirler considering the impeller tip clearance. Test module and Jig facilities for the compressor stage performance test are developed. The overall compressor stage performances measured at the test Jig are compared with aerodynamic design results.