Particle image velocimetry(PIV) was used to experimentally study the cold flow field of a model rectangular trapped vortex combustor(TVC) in this paper.The influence of mainstream velocity and mainstream structure(with or without flame stabilizer) on the behavior of vortex in the cavity was analyzed.It shows that the dimension and shape of vortex
location of vortex center are not sensitive to mainstream velocity.But the swirling strength and circulation mass flow rate in cavity increase with mainstream velocity.The vortex center is located in the center of cavity without stabilizer.The vortex center moves backward at the symmetry section
but moves forward at the stabilizer section.The result can provide references for TVC design and performance optimization.
Numerical simulation on a certain trapped vortex combustor
Study of wall temperature on the interstage turbine single vortex combustor
Experimental study of wall temperature distribution on annular interstage trapped vortex combustor
Effect of lean blowout performance of trapped vortex combustor of the afterburner
Flame structure in supersonic combustion chamber based on 500 Hz OH-PLIF technology,
Related Author
ZHAI Xiao-lei
PENG Ri-liang
FAN Wei-jun
ZHANG Rong-chun
WANG Wei-jian
ZHANG Rong-chun
FAN Wei-jun
XING Fei
Related Institution
Datang International Yungang Thermal Power Limited Liability Company, Datang International Power Generation Corporation Limited
National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics
National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China 2. School of Aeronautics and Astronautics, Zhejiang University
National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China 2. School of Aeronautics and Astronautics, Zhejiang University
National Key Laboratory of Science and Technology on Aero-Engines,School of Jet Propulsion,Beijing University of Aeronautics and Astronautics