Based on three dimensional CFD of single/double-stage lobed mixer-ejector with fixed mixing duct area ratio and length ratio
the effects of fundamental structure parameters on pumping performance were investigated. The results showed that the pumping ratio of double-stage lobed mixer-ejector increased when main stream velocity or lobe diffusion angle rose. The first stage pumping capacity for double-stage lobed mixer-ejector was stronger than single-stage lobed mixer-ejector
meanwhile the total pumping ratio of double-stage lobed mixer-ejector was 100% superior to that of single-stage one. Besides
the maximum vorticity and the velocity circulation became larger with the increase of primary flow velocity. In the direction of main stream
the maximum vorticity of single-stage mixer declined gradually
while the velocity circulation firstly increased and then decreased. However
in the double-stage lobed mixer-ejector
both maximum vorticity and velocity circulation decreased along main stream
with a much higher decreasing speed in the first stage nozzle. What's more
the thermal mixing efficiency declined as primary flow was attached to wall much earlier due to the increase of main stream velocity or lobe diffusion angle. For double-stage lobed mixer-ejector
the thermal mixing efficiency at mixing duct exit section was 6% superior in comparison with single-stage one
though the thermal mixing efficiency of double-stage lobed mixer-ejector rose at a low speed along mixing duct.
Effect of elliptical and compositive cut at trailing edge on the performance of a lobed mixer
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Related Author
LIU You-hong
XIE Yi
GUO Nan
HUANG Shuai
XU Jinglei
WANG Yangsheng
XIE Jian-guang
HUANG Yi-yong
Related Institution
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
China Gas Turbine Establishment, Aviation Industry Corporation of China
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Power and Energy Engineering, Beijing University of Aeronautics and Astronautics
Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China
National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics