The invention relates to a counter-flow flame combustion chamber which has a monocyclic cavity structure. The counter-flow flame combustion chamber is designed by adopting a concept of staged combustion, and combustion gas is supplied from a pre-combustion stage and a main combustion stage, wherein the pre-combustion stage adopts a diffusion combustion structural mode with stable whirlblast, and the main combustion stage adopts a combustion structural mode of combining premixing and pre-evaporation with counter-flow flame. The counter-flow flame combustion chamber mainly comprises a shunt diffuser, an external combustion chamber case shell, an internal combustion chamber case shell, a fuel nozzle, a head pre-combustion stage, a flame tube external wall main combustion stage, a flame tube internal wall main combustion stage, a flame tube external wall and a flame tube internal wall, wherein the head pre-combustion stage utilizes stable flame in a low-speed backflow area, which is generated by whirlblast air entering the combustion chamber from a pre-combustion stage whirlblast assembly; the main combustion stage comprises the flame tube internal wall main combustion stage and the flame tube external wall main combustion stage, and uniform oil-gas mixture jetted from the main combustion stage counters in a flame tube to form a counter jet flow which forms counter-flow flame under the ignition of pre-combustion flame. The invention has simple structure, and can effectively reduce disposal of pollutants besides ensuring the normal work condition of an aeroengine.