the characteristics and design method of ramjet engine combustor with inclined multihole heat shield was researched.First
the temperature distribution of ramjet engine combustor with no-hole heat shield was calculated
and then
according to the temperature distribution
the array of inclined holes in the heat shield (plan A) was designed
after that
the temperature distribution of inclined multihole heat shield was calculated.Using similar methods after two more distribution improvements (plan B and plan C)
the non-uniform distributed solutions of inclined multihole which met the demand for the cooling was obtained.The results show that using the design approach in cooling flow reduced from 17.45% of plan A to 14.99 % of the plan C
the lowest cooling efficiency of inclined multihole heat shield improves from 70% of plan A to 85% of plan C.
Numerical investigation of combination of direct mixing combustion and LPP combustor
Performance test of micro turbojet engine’s evaporator and numerical simulation of the combustor
Numerical study of tangential effusion cooling for combustor liner
Numerical simulation of the flow field in a single annular concentric staged combustor
Numerical prediction of lean blowout in aero-engine combustor
Related Author
LIU Qiang
SUO Jian-qin
LIANG Hong-xia
LI Ming
Li Han
TAN Wen-long
FAN Wei-jun
ZHANG Tao
Related Institution
School of Power and Energy,Northwestern Polytechnical University
National Key Laboratory of Science and Technology on Aero-Engines Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
College of Mechanical Engineering, Nanjing University of Science and Technology