A 16-Inch impulse-type supersdnic-compressor rotor experimentally investigated as a separate component obtained a maximum total-pressure ratio of 5.42 and an adiabatic efficiency of 0.76 at 101-percent design speed. The rotor could be operated over a wide range of back pressures; however, it did not obtain the design impulse condition. At partly closed throttle points, the rotor was able to effect a reduction in equivalent weight flow and total-pressure ratio. This decrease in totalpressure ratio with increased back pressure is a characteristic of a rotor with turning past the axial direction.
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