• The KSFM Journal of Fluid Machinery
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• v.4 no.3 s.12
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• pp.21-28
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• 2001

The effects of diffuser shapes on the flowfields of a small-size turbo-compressor have been investigated numerically and experimentally. The optimal design of elements shapes is important to develop the high efficiency turbo-compressor. Typical range of rotating speed for a small-size turbo-compressor is 40,000-70,000rpm. Numerical analyses were conducted to the rectangular and conical shapes of diffuser Three-dimensional, steady and viscous governing equations were solved by SIMPLE algorithm. To confirm the numerical results, the experimental measurements for the static pressure and temperature at the inlet and outlet boundaries were performed. Comparisons of these results were done, and the reasonable agreements were acquired.

• 유체기계공업학회:학술대회논문집
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• 2001.11a
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• pp.120-125
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• 2001

The effects of various vaned diffuser configurations, such as throat area ratios and rectangular and conical cross-section shapes. to the performance of a small-size turbo-compressor are studied. Numerical analyses were carried out for the region of diffuser and casing only. The pressure recovery coefficient was calculated to estimate the performance of the diffuser, and then compared with the measured data. Results show that the shapes and the throat area ratios of the diffuser strongly influence on the performance of a turbo-compressor.

• 유체기계공업학회:학술대회논문집
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• 2000.12a
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• pp.187-192
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• 2000

The effects of diffuser shapes on the flowfields of a small-size turbo-compressor have been investigated by numerically and experimentally. It is important to optimal design of each elements for developing the small-size turbo-compressor Typical range of rotating speed of a small-size turbo-compressor is 40,000-70,000rpm. Numerical analyses are conducted to the rectangular and conical shapes of diffusers. Three-dimensional, steady, viscous governing equations are solved by SIMPLE algorithm. To prove the numerical results, experimental studies for the measurements of static pressure and temperature at the inlet and outlet boundaries are performed. Comparisons of these results are executed, and reasonable agreements are acquired.

• Journal of the korean Society of Automotive Engineers
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• v.5 no.2
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• pp.1-14
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• 1983

총차량 중량이 15ton이 넘는 대형 트럭의 경우 1970년도에 18%에 불과하던 터보 챠저엔진의 비율은 점차 증가하여 1977년에 42%에 달하였고 1990년도에는 75%까지 증가할 것으로 예상 된다. 또한 현재 터보 챠저엔진의 BMEP는 11.2kg/$cm^{2}$, after cooled엔진은 13.6kg/$cm^{2}$에 이르나 앞으로는 after cooled엔지의 BMEP는 13-17kg/$cm^{2}$로 증대할 것이다. 그러나 터보 챠저엔진의 최대의 단점은 저속에서의 낮은 boost압력과 고속에서의 over boost압력을 갖는다는 것이나, 현재까지는 뚜렷한 해결책을 찾지 못하고 있는 실정이다. 따라서 1980년대에는 현재 사용되고 있는 터보 챠저나 이를 개선한 고성능 터보챠저를 부 착한 엔진이나 after cooled엔진이 주로 사용될 것으로 보인다. 앞으로 터보 챠저가 대형트럭용 엔진에 더욱 확대 사용되고 또 소형 디이젤 엔진이나 가솔린 엔진에서도 이용되기 위해서는 (1) 저속에서의 boost압력 증대 (2) 압력비의 증대 (3) 압축기 사용 flow range의 확대 (4) 소형 터보 챠저의 개발 등이 수반되어야 하며 이외에도 배기가스의 효율적인 에너지전달, 콤푸레샤 효율의 증대, 굉음의 감소, 저렴한 터보 챠저 및 after cooler의 개발, 터보 챠저의 소형화 등이 이루어져야 할 것이다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.10a
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• pp.625-626
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• 2011

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.101-104
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• 2010

Recently, needs for UAVs and small aircraft and small turbo jet or turbo fan engines for these air-crafts are increasing. Size and weight are the two main restrictions in small air-crafts such as UAV or VLJ propulsion system applications. Therefore, high power density is required in small size and designers come up with unconventional solutions in the design of small aero gas turbine engines. One of the solutions is the usage of highly loaded axial compressors. This paper introduces an aerodynamic design method of a highly loaded axial compressor and its review process. Numerical simulation has been carried out to assess the aerodynamic performance of the compressor.

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

• 유체기계공업학회:학술대회논문집
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• 2004.12a
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• pp.434-436
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• 2004

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.40 no.1
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• pp.45-54
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• 2003

Turbo compressor needs high speed rotation of impeller in structure, high rated gearbox and conventional induction motor. This mechanical system increased the moment of inertia and mechanical friction loss. Resently, the study of turbo compressor applied super high speed motor and drive, removing gearbox made its sire small and mechanical friction loss minimum. This paper describes the implementation of the vector control schemes for a variable-speed 131㎾ PMSM(Permanent Magnet Synchronous Motor) drive in super-high speed application.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.4
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• pp.23-32
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• 2012

The present study is aimed to develop an integrated performance analysis approach for the application of a compressor with variable inlet guide vane (VIGV) and vairable stator vane (VSV) in a small turbofan engine. For the integrated analysis approach, an engine performance analysis program, NPSS and a computer program used for predicting of axial flow compressor performance based on stage stacking method, STGSTK were linked with an optimisation package, Isight. This enables off-design performance analysis for the turbofan engine with VIGV and VSV hence provides the capability to predict stable operation condition of the engine with acceptable surge margin.