The invention discloses a
combustion assembly structure of a
turbojet engine. The
combustion assembly structure is characterized in that a guider and a
front cover are arranged at the two ends of a case with a cavity structure in the middle respectively, a shaft sleeve coaxial with the case is fixed to the guider, a diffuser is fixed to the outer ring of the other end of the shaft sleeve, the sections, along the axis of the shaft sleeve, of the connecting faces between guide vanes and the shaft sleeve are in a V shape, the outer ring of the shaft sleeve is provided with a double-layer annularcombustion tank coaxial with the shaft sleeve, the section, along the axis of the shaft sleeve, of the end face of one end of the double-layer annular
combustion tank is V-shaped, the two V-shaped structures enable gas entering from the diffuser to be attached to the wall face of the V-shaped structure of the double-layer annular combustion tank better, meanwhile, the gas entering from the diffuser is prevented from flowing back at a gas inlet, the velocity field is more uniform, the high-speed flow field is optimized, a local high-speed area is avoided, a main combustion area of a combustionchamber can be advanced, and the outlet temperature of the
combustion chamber is further reduced; and the
axial distance between the diffuser and the double-layer annular combustion tank is reduced, so that the total length of the engine is reduced, the weight of the engine is reduced, and
miniaturization of the combustion
assembly of the
turbojet engine is facilitated.