• Title/Summary/Keyword: Turbocompound

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Experimental study on the performance of a turbocompound diesel engine with variable geometry turbocharger

  • Yin, Yong;Liu, Zhengbai;Zhuge, Weilin;Zhao, Rongchao;Zhao, Yanting;Chen, Zhen;Mi, Jiao
    • International Journal of Fluid Machinery and Systems
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    • v.9 no.4
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    • pp.332-337
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    • 2016
  • Turbocompounding is a key technology to satisfy the future requirements of diesel engine's fuel economy and emission reduction. A turbocompound diesel engine was developed based on a conventional 11-Liter heavy-duty diesel engine. The turbocompound system includes a power turbine, which is installed downstream of a Variable Geometry Turbocharger (VGT) turbine. The impacts of the VGT rack position on the turbocompound engine performance were studied. An optimal VGT control strategy was determined. Experimental results show that the turbocompound engine using the optimal VGT control strategy achieves better performance than the original engine under all full load operation conditions. The averaged and maximum reductions of the brake specific fuel consumption (BSFC) are 3% and 8% respectively.

Turbine Design for Turbo-compound System to Recover Exhaust Gas Energy Using 1-D Mean Line Flow Model (1-D Mean Line Flow Model을 이용한 엔진 배기에너지 회수를 위한 터보컴파운드 시스템용 터빈 설계)

  • Jang, Jinyoung;Yun, Jeong-Eui
    • Transactions of the Korean Society of Automotive Engineers
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    • v.24 no.1
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    • pp.74-81
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    • 2016
  • The aim of this study was to find the initial design value of turbine blade for electrical type turbocompound system generating 10 kW. Turbocompound is one of the waste heat recovery system applying to internal combustion engine to recover exhaust gas energy that was about 30 % of total input energy. To design the turbine blade, 1-D mean line flow model was used. Exhaust gas temperature, pressure, flow rate and turbine rotating speed was fixed as primary boundary conditions. The velocity triangles was defined and used to determine the rotor inlet radius and width, the rotor outlet radius at shroud and radius at hub, the rotor flow angles and the number of blades.