An experimental investigation was conducted in an altitude facility to determine the effects of steady-state inlet temperature distortion, pressure distortion, and combined temperature and pressure distortion on the stability of a PW1128 turbofan engine. The steady-state temperature distortion was generated by a gaseous-fueled hydrogen burner. Pressure distortion was produced by a screen installed in the inlet ducting between the burner and the engine inlet. With the exceptions of inlet pressure distortion, a tip-radial inlet temperature distortion at the highest corrected fan speed tested, and combined distortion with the low-pressure and high-temperature regions together, the fan generated a flow instability when operating near its steady-state stall line. In some instances the fan was not the first component to surge, however, because the instability disrupted the flow to the high-pressure compressor causing it to surge at, or near, the same time as the fan. The effect of combined distortion was dependent on the relative locations of the high-temperature and low-pressure regions; high-pressure compressor stall occurred when the distorted regions were together, and fan stall occurred when the distorted regions were diametrically opposed.


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    Titel :

    Effect of spatial inlet temperature and pressure distortion on turbofan engine stability


    Weitere Titelangaben:

    Einfluss von raeumlichen Stoerungen der Einlasstemperatur und des Drucks auf die Stabilitaet von Turbopropmaschinen


    Beteiligte:
    Mehalic, C.M. (Autor:in)

    Erschienen in:

    AIAA-Papers ; Jul ; 1-15


    Erscheinungsdatum :

    1988


    Format / Umfang :

    15 Seiten, 20 Bilder, 2 Tabellen, 23 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch





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