• 한국전산유체공학회:학술대회논문집
• /
• 2010.05a
• /
• pp.142-146
• /
• 2010

This study presents the design of small size turbo-compressor to increase the performance using computational fluid analysis. A three dimensional computation was conducted changing the main parameters of impeller blade and diffuser shape, respectively, and the design was performed on a basis analysis of result of that. As a result, the Improved shapes show the increase of efficiency in comparison with the existing shape. This study will be used as useful reference data to establish the design concept of the small size turbo-compressor and to improve its performance.

• The Transactions of the Korean Institute of Electrical Engineers B
• /
• v.54 no.6
• /
• pp.278-286
• /
• 2005

Recently, high-speed centrifugal turbo-compressors have been under intensive research and development. Since, compared to conventional compressors, high-speed centrifugal compressors hive numerous qualities such as simple structure, light weight small size, and high efficiency, etc. In cope with such industrial demands, a high-speed brushless DC motor for a 50-kW, 70-krpm turbo-compressor was developed based on a 2-D analytical method, of which design was verified using the FE analysis. A prototype machine was also fabricated and tested to confirm the analytical design. Preliminarily obtained experimental data using the prototype mac]line shows the validity of the analytical approach.

• 한국전산유체공학회:학술대회논문집
• /
• 2010.05a
• /
• pp.129-130
• /
• 2010

Design of turbo-compressors has been considered to be a high-tech which only a few early industrialized countries could do efficiently since it requires not only deep understanding of high level gas dynamics and complex fluid dynamics but also accumulation of experiences in the feedback of expensive manufacturing and difficult testing to the design theory and empirical design coefficients. CFturbo is the turbomachinery design software which incorporates traditional well formulated German design technology and latest software technology of 3-dimensional graphics. Fine/Turbo is a powerful tubomachinery-oriented CFD package with quality structured grid topology templates for almost all the tubomachinery configurations for easy, fast and accurate CFD analysis. Rapid and effcient process off turbo-compressor R&D is setup with the combination of CFturbo and Fine/Turbo.

• Proceedings of the KSME Conference
• /
• 2001.06e
• /
• pp.807-812
• /
• 2001

The effects of casing shapes on the interaction of the impeller and volute in a small-size turbo-compressor are investigated. Numerical analysis is conducted for the compressor with circular and single volute casings from inlet to discharge nozzle. In order to predict the flow pattern inside the entire impeller, vaneless diffuser, and casing, calculations with a multiple frame of reference method between the rotating and stationery parts of the domain are carried out. For incompressible turbulent flow fields, the continuity and three-dimensional time-averaged Navier-Stokes equations are employed. To predict the performance of two types of casings, the static pressure and loss coefficients are obtained with various flow rates. Also, static pressure distributions around casings are studied for different casing shapes, which are very important to predict the distribution of radial load.

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2013.05a
• /
• pp.1099-1100
• /
• 2013

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2009.06a
• /
• pp.491-492
• /
• 2009

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2010.11a
• /
• pp.931-932
• /
• 2010

• New & Renewable Energy
• /
• v.1 no.4 s.4
• /
• pp.30-37
• /
• 2005

Cycle simulation of Ground Source Heat Pump[GSHP] system was carried out to determine the design specification of basic components such as turbo compressor and heat exchangers. Part load operation characteristics of the designed GSHP system was estimated using the compressor and heat exchanger performance data. A 50RT class turbo compressor for GSHP system is now under development, in which R134a refrigerant is adopted as working fluid. The compressor with variable cascade diffusers is designed to work both in cooling and heating modes so that it can actively keep up with the climate change with high efficiency. The normal running speeds of the compressor are 59000rpm for heating mode and 70000rpm for tooling mode respectively. It has two identical impellers at both ends of the rotor so as to minimize aero-induced thrust force effectively. GSHP system was coupled with a vortical type heat exchanger, and heat gain and heat loss from ground were evaluated per a bore hole. For the optimal integration of the heat pump system, its header for circulating fluid was combined with the ground heat exchangers in parallel and series configuration.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.05a
• /
• pp.222-226
• /
• 2006

The purpose of this study is to analyze both the design and off design performance simulation of the PW206C turbo shaft engine used in the development of the smart UAV (Unmanned Ariel Vehicle) by KARI(Korean Aerospace Research Institute). Its mainly aims to investigate performance behavior at the un-installed and installed conditions. The ways employed to be able to analyze the performance extensively were mainly carried out by comparison of performance simulation results from both the commercial program 'GASTURB 9' using compressor maps generated by Genetic algorithms (GAs) or Scaling Method, and the engine manufacturer's program 'EEPP'. Off-design performance analysis was performed through matching of both mass flow and work between engine components. The set of performance simulations of the developed analytical models was performed by a commercial program package (GASTURB 9) that provides great flexibility in the choice of independent variables of the overall system. The results from the simulations are used to compare turbo shaft engine (PW206C) performance data obtained by the EEPP. At un-installed condition, it was found that the results with the compressor map generated by GAs were relatively agreed well than those with the compressor map generated by the Scaling Method. The performance calculation results using the compressor map generated by GAs were compared at un-installed condition and installed conditions with ECS-off and ECS-Max in variation of altitude, gas generator speed and flight speed.

• Proceedings of the KSME Conference
• /
• 2008.11b
• /
• pp.2621-2624
• /
• 2008

The study on the measurement method of the aerodynamic performance of a turbo compressor was conducted. It is well known that the performance and the efficiency of the compressor can be calculated from the temperature and pressure distribution in each stage of the compressor. In the past Pitot tubes and thermocouples were used to measure pressure and temperature respectively, and recently pressure and temperature rake is used in order to decrease the measuring time and the number of measurement. The miniature total pressure rake which is available in the compressor with a small axial gap is designed and is under development.