JOURNAL OF THE MARINE ENGINEERING SOCIETY IN JAPAN
Online ISSN : 1884-4758
Print ISSN : 0388-3051
ISSN-L : 0388-3051
Volume 4 , Issue 2
Showing 1-6 articles out of 6 articles from the selected issue
  • [in Japanese]
    1969 Volume 4 Issue 2 Pages 61-70
    Published: 1969
    Released: May 31, 2010
    JOURNALS FREE ACCESS
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  • [in Japanese], [in Japanese]
    1969 Volume 4 Issue 2 Pages 71-74
    Published: 1969
    Released: May 31, 2010
    JOURNALS FREE ACCESS
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  • [in Japanese], [in Japanese], [in Japanese]
    1969 Volume 4 Issue 2 Pages 75-79
    Published: 1969
    Released: May 31, 2010
    JOURNALS FREE ACCESS
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  • [in Japanese]
    1969 Volume 4 Issue 2 Pages 80-86
    Published: 1969
    Released: May 31, 2010
    JOURNALS FREE ACCESS
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  • Masashi Nagai, Tadataka Asada
    1969 Volume 4 Issue 2 Pages 87-100
    Published: 1969
    Released: May 31, 2010
    JOURNALS FREE ACCESS
    To obtain adjustments, in the case of comparing performances of a turbocharged two-cycle diesel engine operating under different conditions of atmospheric pressure, temperature, scavenging air temperature, maximum combustion pressure or turbine back pressure, we developed a set of approximate theoretical equations for the turbocharged two cycle diesel engine under the following assumptions.
    (1) The exhaust gas turbine is treated as a pulse-type, and the exhaust blow down energy is considered as the theoretical exhaust blow down energy multiplyed by a coefficient introduced by the author, called utility coefficient.
    (2) For the gas flow between the turbine nozzle and the reduced port of the scavenging and exhaust port, the equilibrium relation is considered as the equivalent flow of the gas and the air volume.
    (3) The gas exchange in the scavenging period is in the middle stage of perfect mixing and perfect alienating; the heat exchange is in the middle of initial scavenging state and the final scavenging state.
    (4) The cycle in the engine cylinder is treated as a composite cycle. The compression and expansion indices, and constant pressure expansion ratio are determined depending upon the assumption that the pressures of the compression start and end point, and of the end point in the main combustion agree with those of the real cycle.
    More over, the specific heat of the gas is a function of the gas temperature and the composition.
    The developed equations several conditions of the cycles are simulated for comparison by means of a digital computer. And using the calculated results explain how the performance and cycle factors of the engine are affected by such conditions as atmospheric temperature and pressure, scavenging air temperature or cooling condition of the air cooler, muximum combustion pressure or fuel injection timing, turbine back pressure or flow passage area of the silencer.
    At the same time, we investigate the influence of the turbine and the compressor efficiency, and of the turbine nozzle area.
    The developed equations agreed with actual operating results. The equation can be used for a diesel engine in different conditions or two engines of similar types in different conditions.
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  • Hiroshi Masago, Takao Motooka, Junichi Arai
    1969 Volume 4 Issue 2 Pages 109-115
    Published: 1969
    Released: May 31, 2010
    JOURNALS FREE ACCESS
    The authors measured the dynamical stresses and axial displacements of crankshaft for the propulsion system of the Diesel ship, of which only torsional vibration resonance was altered and axial vibration resonance remained in itself.
    The results were summarized as follow
    1) When torsional vibration resonance decrease from 1.14 to 1.10 times of axial one, the axial displacement and fillet bending stress at torsional vibration resonance increase to 1.3 and 1.4-1.9 times, respectively.
    2) Mode curves of axial displacement obtained by measurements at axial vibration resonance accord wits one by calculation, but at torsional one do not.
    3) Two resonance for 1 and 2 nodes axial vibration was found but additional stress for the fornaer is very larger than for the latter, thorgh the calculated exiting force are equal.
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