Low Noise Research Fan Stage Design

摘要: This report describes the design of a Low Noise ADP Research Fan stage. The fan is variable pitch which designed at cruise condition. Relative to setting, blade closed takeoff and opened for reverse thrust operation. stage split flow with exit guide vanes core stators. was combined nacelle engine duct form powered fan/nacelle, subscale model. model intended use in aerodynamic performance, acoustic structural testing wind tunnel. has 22-inch outer diameter hub-to-top ratio 0.426 permits existing NASA cowl force balance designs rig drive system. parameters were selected permit valid comparisons PW 17-inch previously tested under contract. described detail. results axisymmetric analysis condition are included. rotor attachment including material selections stress analysis. predicted have adequate low cycle fatigue life, an acceptable operating range without resonant or flutter. acoustically airfoil counts vane stator minimize noise. A fan-FEGV tone developed separately contract used determine these counts. matched fan/nacelle tunnel testing. separate inlet, nozzle convenience fabrication. Aerodynamic confirmed required performance various aircraft conditions.