Identification and Reduction of Turbomachinery Noise

Communities near airports are often exposed to high noise levels due to low flying aircraft in the takeoff and landing phases of flight. Propulsion source noise is the major contributor to the overall noise level. The noise generation mechanisms for a typical turbofan engine are complicated, which makes it a significant challenge to identify the noise sources. Each engine component, such as fan, compressor and turbine, can generate both broadband and narrowband noise. Particularly, the fan noise, more specifically the interaction of the rotor with the downstream stator, is important due to the trend towards the development of civil aircraft turbofan engines with higher and higher by pass ratios. Nearfield acoustical holography (NAH) refers to a process by which the noise sources and the resulting sound field can be reconstructed based on sound pressure measurements taken on a surface in the neighborhood of these sources. Thus, the development and application of appropriate generalized acoustical holography (GAH) system by extending NAH to handle arbitrary geometry and complex noise sources, novel measurement and data processing methods, and innovative inversion and regularization techniques will conceptually allow the identification and ranking of complex turbomachinery noise sources that are otherwise difficult to characterize. This system will also enable the use of more effective active and/or passive noise control measures by providing useful information that is impossible to obtain by direct measurements.