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Wednesday, July 10 • 15:30 - 15:50
MODAL DECOMPOSITION TECHNIQUE OF SOUND FIELD IN DUCT USING COMPUTATIONAL EXPERIMENT

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Reducing aircraft noise continue to be relevant and form an important part of the overall problems of ensuring environmental safety. Experimental analysis of sound fields generated by an aircraft engine is one of the most important and complex problems of aviation acoustics. The main difficulty is the large number of acoustic modes emitted by the engine. The chief part of energy-efficient acoustic modes is generated by the fan of the engine. The most advanced technique for analyzing sound field generated by the fan is modal analysis in the intake and bypass of the engine. A special mathematical model is being developed in the present paper to optimize modal decomposition technique. The presented model represents a calculation of sound propagation in the engine intake using the Navier-Stokes equations and numerical schemes of high-order accuracy. The test object is a cylindrical intake duct. The entire lower surface inside the duct was used for sound field generation, setting unsteady pressure as a combination of acoustic modes. The modes were registered at the points of the ring array and at gross sections inside the duct that were located at the same distance from the bottom surface. The technique of modes registration at gross sections allows to identify all the modes generated inside the duct, because it uses complete information in the section and real experimental measurements are imitated by measurements at points. This paper presents the calculation of sound propagation in the cylindrical intake. It contains the calculation results with different combinations of modes and there is a comparison of modal decomposition based on points and gross sections measurements. In terms of the presented analysis problems in the experimental modal decomposition have been identified and the ways of their elimination have been outlined.


Wednesday July 10, 2019 15:30 - 15:50 EDT
Outremont 5
  T03 Aero… aircrft noise & vibr., SS02 Computational Aeroac