• Title/Summary/Keyword: 나비어-스톡스방정식

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Performance Analysis of a Centrifugal Fan with Splitters (수치해석에 의한 스플리터 부착 원심송풍기 성능특성 연구)

  • Jang, Choon-Man;Choi, Ka-Ram;Yang, Sang-Ho
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.35 no.10
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    • pp.1067-1073
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    • 2011
  • This paper describes the performance of a centrifugal fan used for refuse collection systems according to the chord length of the splitters installed near the blade suction and pressure surface sides. The fan performance is analyzed by three-dimensional Navier.Stokes analysis and is compared to the results obtained experimentally. Throughout the numerical simulation of the fan with splitters, it is found that the reverse-flow region observed near the suction side of the blade can be reduced by installing a splitter. The fan performance is successfully improved by controlling the chord length of the splitter installed near the blade suction side. Under the designed flow condition, the efficiency and pressure of a fan with splitters increase by up to 4% and 18%, respectively, compared to the reference fan.

The Effect of Gas Thermochemical Model on the Flowfield of Supersonic Rocket in Propulsive Flight (기체 열화학 모델이 연소 비행하는 초음속 로켓 유동장에 미치는 영향)

  • 최환석
    • Journal of the Korean Society of Propulsion Engineers
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    • v.6 no.1
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    • pp.12-20
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    • 2002
  • An integrated analysis of kerosine/LOX based KSR-III rocket body/plume flowfield has been performed. The analysis has been executed employing three kind of gas thermo-chemical models including calorically perfect gas, multiple species chemically reacting gas, and chemically frozen gas models and their effect on rocket flowfield has been accessed to provide the most appropriate gas thermo-chemical model which meets a specific purpose of performing rocket body and plume analysis. The finite-rate chemically reacting flow solution exhibited higher temperature throughout the flowfield than other gas models due to the increased combustion gas temperature caused by the chemical reactions within the nozzle. All the reactions were dominated only in the shear layer and behind the barrel shock reflection region where the gas temperature is high and the effect of finite-rate chemical reactions on the flowfield was found to be minor. However, the present plume computation including finite-rate chemical reactions revealed major reactions occurring in the plume and their reaction mechanisms and as well.