The effects of engine configuration, advanced component technology, compressor pressure ratio and turbine rotor-inlet temperature on such figures of merit as vehicle gross weight, mission fuel, aircraft acquisition cost, operating, cost and life cycle cost are determined for three fixed- and two rotary-wing aircraft. Compared with a current production turboprop, an advanced technology (1988) engine results in a 23 percent decrease in specific fuel consumption. Depending on the figure of merit and the mission, turbine engine cost reductions required to achieve aircraft cost parity with a current spark ignition reciprocating (SIR) engine vary from 0 to 60 percent and from 6 to 74 percent with a hypothetical advanced SIR engine. Compared with a hypothetical turboshaft using currently available technology (1978), an advanced technology (1988) engine installed in a light twin-engine helicopter results in a 16 percent reduction in mission fuel and about 11 percent in most of the other figures of merit.


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    Titel :

    Preliminary study of advanced turboprop and turboshaft engines for light aircraft


    Beteiligte:
    Knip, G. (Autor:in) / Plencner, R. M. (Autor:in) / Eisenberg, J. D. (Autor:in)

    Erscheinungsdatum :

    01.04.1980


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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