Gas turbine and aircraft engine combustor tail cylinder structure

The invention discloses a gas turbine and aircraft engine combustor tail cylinder structure. The structure comprises a support ring, a tail cylinder body and an outlet flange; the support ring is mounted at the front end of the tail cylinder body; and the outlet flange is mounted at the back end of the tail cylinder body. The structure is characterized in that the tail cylinder body is formed by connecting multiple sections of high-temperature alloys with different high-temperature resisting performances; and according to the metal temperature distribution tendency, the part with higher temperature is a material with higher high-temperature resisting performance, and the part with lower temperature is a material with weaker high-temperature resisting performance. The structure not only can exert the mechanical performances of the materials to the greatest extent, but also can greatly reduce the tail cylinder production cost, and in particular, is suitable for design of traditional gas turbine (aircraft engine) combustor tail cylinders with higher temperature.