Abstract
A test platform was developed to investigate the performance of aero-engine combustor by the dielectric barrier discharge (DBD) plasma assisted combustion (PAC) in the simulated maximum condition. Conventional combustion experiments and plasma-assisted combustion conditions were conducted to study the effect of PAC on the performances including average outlet temperature, combustion efficiency and pattern factor under four different excessive air coefficients five different voltages. The comparative experiment shows that the combustion efficiency is improved after PAC compared with the normal conditions, the combustion efficiency of PAC increases 2.31% in the fuel-rich condition when Up-p is 40 kV. The uniformity of the outlet temperature field is also improved after PAC, the decrease of the pattern factor is more than 5% in the fuel-rich condition. These results offer certain reference value for the future application of PAC in aero-engine combustor and improving its performance.
Highlights
本文中,燃烧效率定义如下: ηc mf ) cpgas Tout - ma cpa Tin Hμmf mf cpf Tf
A test platform was developed to investigate the performance of aero⁃engine combustor by the dielectric barrier discharge ( DBD) plasma assisted combustion ( PAC) in the simulated maximum condition
Conventional combustion experiments and plasma⁃assisted combustion conditions were conducted to study the effect of PAC on the performances including average outlet temperature, combustion efficiency and pattern factor under four different ex⁃ cessive air coefficients five different voltages
Summary
本文中,燃烧效率定义如下: ηc mf ) cpgas Tout - ma cpa Tin Hμmf mf cpf Tf Experimental Study on Lean Blowout of a High Temperature Rise Combustor[ C] ∥55th AIAA Aerospace Sciences Meeting, 2017 Plasma Assisted Ignition and Combustion[ J] .
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