Accession Number : AD0617936

Title :   COMPRESSOR NOISE RESEARCH.

Descriptive Note : Final technical rept.,

Corporate Author : BOEING CO RENTON WA AIRPLANE DIV

Personal Author(s) : Bateman, David A. ; Chang, Stephen C. ; Hulse, Bruce T. ; Large, John B.

Report Date : JAN 1965

Pagination or Media Count : 103

Abstract : The noise generating mechanisms of axial flow compressor blades were investigated using flat blades to facilitate mathematical analysis. Analytical expressions are given for evaluating the compressor noise due to blade thickness, loading and vortex shedding. Measured values of compressor noise show good agreement with those analytically predicted. It was found that lift or loading noise dominates over blade thickness and vortex noise. Rotor-stator spacing and clearance between the rotor blade tips and the duct are important parameters in the generation of rotor noise. (Author)

Descriptors :   *JET ENGINE NOISE, *AXIAL FLOW COMPRESSOR BLADES, *COMPRESSOR NOISE, AXIAL FLOW COMPRESSORS, NOISE ANALYZERS, AERODYNAMIC LOADING, LIFT, THICKNESS, COMPRESSOR ROTORS, COMPRESSOR STATORS, TOLERANCES(MECHANICS), FLUID FLOW, MATHEMATICAL ANALYSIS, AERODYNAMIC CHARACTERISTICS, JET ENGINE INLETS.

Distribution Statement : APPROVED FOR PUBLIC RELEASE