Exploratory Research into Turbofan Stability Performance. Volume I.

摘要

A redesigned Low Pressure-Intermediate Pressure (LP-IP) compressor system was tested to determine the improvement in performance over the original design and to assess the dependence of compressor system stability on the blade design changes. Tests were conducted in a dual throttle facility with undistorted inlet flow and with three distortion patterns:hub radial,tip radial,and 180-degree circumferential. All undistorted inlet design goals were met with the exception of bypass ratio.