Variable immersion lobe mixer for turbofan jet engine exhaust and manufacturing method thereof

摘要

A method of manufacturing a mixer for a gas turbine engine is provided. The method includes forming a front end and a rear end of the mixer, and forming an annular wavy profile defining a plurality of core immersion lobes and a plurality of bypass immersion lobes between the front end and the rear end. Including the step of. The plurality of bypass immersion lobes comprise a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe includes a first top contour line extending from the front end of the mixer to the rear end, and a second bypass immersion lobe extends from the front end of the mixer to the rear end. Includes a second top contour. The first top contour line is different from the second top contour line. [Selection] Figure 1