径向旋流器中速度检测方案(激光干涉仪)

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    The efficiency of modern Gas Turbine can be increased by accelerating the atomizationand evaporation of liquid fuel injected into the combustor. Chevrons mixers, seen in service on today’s advanced jet engines, generate streamwise vorticity off of the chevron tips which is able to quickly mix two separate flows and reduce the exhaust noise of these engines. The enhanced mixing ability of a chevron exhaust nozzle motivated the investigation of chevrons a typical combustion swirling flow, where fuel-air mixing is a limiting factor of the combustion system’s performance.     The focus of this research is to experimentally investigate the isothermal aerodynamicand multi-phase flow properties of radial-radial counter rotating swirl cups with chevron mixinggenerators. Each swirl cup assembly features a primary swirler with a converging-divergingventuri, secondary swirler, exit flare with a 72° expansion angle, and a simplex fuel nozzle with a flow number of 0.7 and spray angle of 80°. Six unique trailing edge designs were applied to the primary swirler: four chevron designs, one shortened venturi, and one baseline. Confined and unconfined aerodynamic studies by 2D Laser Doppler Velocimetry was coupled with flow visualization and 2D Phase Doppler Interferometry to characterize the single and multi-phase flow properties of the different trailing edge designs.