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Variable immersion lobe mixer for turbofan jet engine exhaust and manufacturing method thereof
Variable immersion lobe mixer for turbofan jet engine exhaust and manufacturing method thereof
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机译:用于涡扇喷气发动机排气的可变浸入式叶片混合器及其制造方法
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摘要
A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end. The plurality of bypass immersion lobes includes a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe has a first crown contour line extending from the forward end to the aft end of the mixer, and the second bypass immersion lobe has a second crown contour line extending from the forward end to the aft end of the mixer. The first crown contour line is different than the second crown contour line.
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