Gas turbine hot end cooling structure and gas turbine with same

The invention relates to a gas turbine hot end cooling structure and a gas turbine with same. An annular cooling cover plate is arranged on an annular elbow pipe, the reverse side of the cooling cover plate is provided with a ribbed plate channel, cooling airflow introduced by a cooling airflow hole in the annular elbow pipe shocks the reverse side of the cooling cover plate to rapidly cool the cooling cover plate, and the fuel gas temperature surrounding the front of the cooling cover plate is lowered at the same time; then the cooling airflow flows to the downstream to cool an installation edge of a gas turbine guider. Since the ribbed plate channel in the reverse side of the cooling cover plate plays a role as approximately a pressure stabilizing cavity, the cooling airflow can be uniformly mixed, a layer of cooling gas film is formed on the surface of the installation edge of the guider, and thus the cooling effect is greatly improved. The cooling airflow continues to flow to downstream, and thus a protective effect is also formed on an externally flow channel surface of the gas turbine guider. Through the adoption of the structure, the turbine cooling effect can be obviously improved, the service life of the turbine is prolonged, and the service life of the gas turbine guider is particularly prolonged.