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- 저자 : 김용련(Yong Ryun Kim) (검색결과 1 건)
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최재호(Jae Ho Choi),한착희(Chak Heui Han),팽기석(Ki Seok Paeng),전승배(Seung Bae Chen),김용련(Yong Ryun Kim) 대한기계학회 2005 대한기계학회 춘추학술대회 Vol.2005 No.11
This paper presents an aerodynamic design, flow analysis and performance test of a pressure ratio 4:1 centrifugal compressor for gas turbine engine. The compressor is made up of a centrifugal impeller, a two-stage diffuser consisted of radial and axial types. The impeller has a 45 degree backswept angle and the design running tip clearance is 5% of impeller exit height. Three-dimensional numerical analysis is performed to analyze the flows in the impeller, diffuser and deswirler considering the impeller tip clearance. Test module and rig facilities for the compressor stage performance test are designed and fabricated. The overall compressor stage performances as well as the static pressure fields on the impeller and diffuser are measured. Two diffusers of wedge and airfoil types are tested with an impeller. The calculation and test results show that flow fields downstream the deswirler at the design and off-design points are highly nonuniform and the airfoil diffuser has the better aerodynamic characteristics than those of wedge diffuser.
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