The role of the central plug in promoting the thermal mixing between the primary and the secondary flows of the circularly lobed nozzle was assessed mainly by the numerical simulation.The fundamental equations were derived in the body fitted nonorthogonal coordinates from cylindrical coordinates for the circularly lobed exhaust ejector mixers with/without a plug in the center of the lobe.These equations were solved using SIMPLEC and a kind of complete pressure correction algorithm in the nonstaggered grids
with the velocity components in physical plane as solving variables and the contravariant velocity components as boundary velocities of the controlled volume.Better agreements have been observed between the numerical results and the experimental values.The numerical results show that there are great differences between the temperature contour in the outer section of the column mixer with the plug in which the low temperature contour lines can reach the center line of the mixer
and that in the outer section of column mixer without the plug in which the elevated temperature contour lines always lie in the central zone.This is the basic reason why the thermal mixing efficiency of the mixer with the plug is much more than that of the mixer without the plug.
Numerical study on aerodynamic performance of multi-stage lobed mixer-ejector
Effect of width of skirted mixer on performance of mixing diffuser with par-allel intake
Effect of lobe number on aerothermodynamic performance of lobed S-shaped two-dimensional nozzle
Effect of inlet preswirl on the aerothermodynamic performance of splitter mixing exhaust system
Mixing characteristics of hyperburner with a lobed mixer
Related Author
ZHANG Jin-zhou
FU Jun
TAN Xiao-ming
CHEN Geng
XIE Jian-guang
HUANG Yi-yong
ZHONG Shi-lin
XU Hua-sheng
Related Institution
Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing 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