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145RT 급 냉동기용 2 단 터보냉매압축기의 공력설계 및 성능시험
박준영(JunYoung Park),황순찬(SoonChan Hwang),김욱중(OokJoong Kim),박무룡(MooRyong Park),윤의수(EuiSoo Yoon),황준현(JoonHyeon Hwang),최상규(Sangkyu Choi) 대한기계학회 2011 대한기계학회 춘추학술대회 Vol.2011 No.10
Two stages centrifugal compressor using R134a as working fluid for a 145RT class chiller has been developed. Each stage of Centrifugal compressors is connected by return channel. An aerodynamic design was done by applying the repeating design procedure including a meanline design, a 3D geometry generation and fluid dynamic calculation. The performance test was also conducted by the experiment. So, in this paper, design, performance prediction and experiments results for two stages turbo refrigerant compressor will be presented.
박준영(JunYoung Park),황순찬(SoonChan Hwang),박무룡(MooRyong Park),안국영(KookYoung Ahn) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.11
This study is concerned with centrifugal compressor design of a turbo generator system, which is used for maximizing performance of a 250㎾ MCFC fuel cell system. The centrifugal compressor consists of an impeller, two vaneless diffuser, a vaned diffuser and a volute. A aerodynamic design was done by applying the repeating design procedure including a meanline design, a 3D geometry generation and fluid dynamic calculation. In this paper, design and performance prediction results of the centrifugal compressor are presented.
박준영(JunYoung Park),박무룡(MooRyong Park),황순찬(SoonChan Hwang),안국영(KookYoung Ahn) 대한기계학회 2009 대한기계학회 춘추학술대회 Vol.2009 No.5
This turbo blower is developed as an air supply system in 250 ㎾ MCFC system. The turbo blower consists of an impeller, two vaneless diffusers, a vaned diffuser and a volute. The three dimensional, steady state numerical analysis is simultaneously conducted for the impeller, diffuser and volute to investigate the performance of total system. To consider the non-uniform condition in volute inlet due to volute tongue, full diffuser passages are included in the calculation The results of numerical analysis is validated with experimental results of thin blade thickness. Total pressure ratio, efficiency, slip factor and blade loading are compared in two cases. The slip factor is different in two cases and the comparison of two cases shows a good performance in thin blade thickness in all aspects.
박준영(Jun Young Park),박무룡(MooRyong Park),황순찬(SoonChan Hwang),최범석(BumSuk Choi) 대한기계학회 2008 대한기계학회 춘추학술대회 Vol.2008 No.5
Axial-flow compressor is one of the most important parts of gas turbine units with axial turbine and combustor. Therefore, precise prediction of performance is very important for development of new compressor or modification of existing one. Meanline analysis is a simple, fast and powerful method for performance prediction of axial-flow compressors with different geometries. So, Meanline analysis is frequently used in preliminary design stage and performance analysis for given geometry data. Much correlations for meanline analysis have been developed theoretically and experimentally for estimating various types of losses and flow deviation angle for long time. In present study, meanline analysis program was developed to estimate compressor losses, incidence angles, deviation angles, stall and surge conditions with many correlations. Performance prediction of one stage axial compressors is conducted with this meanline analysis program. The comparison between experimental and numerical results show a good agreement. This meanline analysis program can be used for various types of single stage axial-flow compressors with different geometries, as well as multistage axial-flow compressors.