The invention discloses
turbine-based
combined cycle engine super-
combustion chamber. Key parts of the super-
combustion chamber comprise a shunt ring, a rear area-variable deflation valve, a flow guide tongue piece, a square lobe mixer, a first area fuel ejector, a center cone, a second area
fuel injection ring, an
evaporation tube
flame stabilizer, a heat-isolating screen, a super-
combustion chamber cylinder, an outer extending groove-width-variable radial
flame stabilizer and an inner extending radial
flame stabilizer. An internal flow field of the super-
combustion chamber is reasonably distributed, the phenomenon of
backflow from a
punching duct to a
turbofan duct can not occur, flow separation can not occur in the square lobe mixer, and the
evaporation tube flame stabilizer can achieve soft ignition of the super-
combustion chamber. The whole super-
combustion chamber is high in mixing efficiency, little in cold flow resistance, high in combustion efficiency, reasonable in temperature distribution, and capable of meeting use requirements in a whole
flight envelope of the super-combustion chamber in each work state and the requirement for boost of an
turbofan ramjet.