The gas turbine Engine is universally used in military aircraft because it is simple, lightweight, and reliable. However, the small engine (500 hp category) has a specific fuel consumption (SFC) generally above 0.6 (pounds of fuel per brake horsepower hour). Future improvements will decrease th 500 shaft horsepower engine to an SFC of 0.43. However, the adiabatic diesel has demonstrated an SFC of only 0.285. This is a reduction of 52 % over existing engines and, compared to future engines, a savings of 41 % is possible, so why stay with the gas turbine engine? Well, other requirements must also be satisfied. For example, how heavy can the engine be? A computation using the Blackhawk helicopter as an example shows the allowable specific weight of the engine to be 0.76 lb/hp. This computation is based on allowing the engine to increase in weight to offset fuel, tankage, and support weight saved such that the take-off gross weight of the aircraft is not changed. This is felt to be attainable and examples of paper designs available in the literature are briefly discussed. This preliminary study indicates that the Army helicopter fleet fuel consumption could be reduced by more than 40 % if it could be retrofitted with adiabatic compound diesel engines. (Wassmann)


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    Title :

    Preliminary survey of possible use of the compound adiabatic diesel engine for helicopters


    Additional title:

    Vorlaeufiger Ueberblick ueber die moegliche Anwendung des adiabatischenCompound-Dieselmotors fuer Hubschrauber


    Contributors:

    Published in:

    Publication date :

    1982


    Size :

    7 Seiten, 10 Bilder, 4 Tabellen, 9 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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