Parametric Blade Study Test Report Rotor Configuration. Number 4
Final rept. 1 Jan 87-31 May 88,
AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH
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The results of an experimental evaluation of one compressor test of a series of design parameter investigations are presented. The purpose of the parametric blade design study was to investigate the effects of specific rotor blade design parameters on the performance of one compressor configuration of current interest with state-of-the-art performance. It was the intent of the program to vary only one design parameter at a time, keeping the other parameters as closely as possible to their original baseline design values. Design parameters investigated were the chordwise location of maximum blade thickness, suction surface blade shape, effective blade camber, and blade leading edge sweep. Experimental performance and detailed aerodynamic analysis results are presented. Keywords Axial compressor, Gas turbine, Aircraft turbine engine.