Abstract
Self-noise from fans and rotors is generated by blade boundary-layer turbulence interacting with the trailing edges of the blades. Previous theories describing this mechanism have considered only an isolated airfoil and have shown that acoustic scattering from the sharp trailing edge is responsible for the sound that propagates to the far e eld. In aeroengine applications, fans or stators have relatively high solidity, and there will be acoustic scattering from adjacent blades as well as the blade locally excited by the e ow. The theory is given for self-noise from a fan modeled as a linear cascade of semi-ine nite e at plates. The magnitude of the self-noise mechanism is compared with the e eld that would be generated by a single airfoil without adjacent blade scattering.
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