For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.


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    Titel :

    Comparison of Performance and Component Frontal Areas of Hypothetical Two-spool and One-spool Turbojet Engines


    Beteiligte:

    Erscheinungsdatum :

    17.01.1956


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch