Effect of Steady-State Pressure Distortion on Inlet Flow to a High-Bypass-Ratio Turbofan Engine

Download or read book Effect of Steady-State Pressure Distortion on Inlet Flow to a High-Bypass-Ratio Turbofan Engine written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-14 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static pressure and total pressure distributions were measured in the inlet duct upstream of the engine inlet and within the fan and compressor of a YTF34 turbofan engine. In addition, the free stream flow angle was measured between the distortion generator and the engine inlet. Distortions were generated using three screen configurations with extents of 90 deg or 180 deg. The screens were mounted on a rotatable screen assembly. Reynolds number index upstream of the distortion device was maintained at 0.5 or 0.2, and engine fan speed corrected to station 2 temperature was maintained at 80 or 90 percent of rated condition (7005 rpm). Flow angle was nearly constant near the distortion device and increased as flow approached the engine inlet. The largest flow angle occurred in the hub region of the engine inlet. Static pressure distortion along the inlet duct increased exponentially as the flow approached the engine. Both static pressure and total pressure distortions were attenuated between engine inlet and compressor exit. Soeder, R. H. and Bobula, G. A. Glenn Research Center NASA-TM-82964, E-1383, NAS 1.15:82964, AVRADCOM-TR-81-C-27 RTOP 505-32-6A...