gas turbine combustor

Abstract

The invention relates to the technical field of a gas turbine, and particularly discloses a combustion chamber of the gas turbine. The combustion chamber comprises a combustion pressure cylinder, a turbine box, an end cover, a spray nozzle, a flow guiding bush, a flame tube and a transition section, wherein the rear end of the turbine box is connected with the combustion pressure cylinder, the end cover is connected to the front end of the turbine box, the spray nozzle is connected to the end cover, the flow guiding bush is connected to the inner side of the turbine box, the flame tube is positioned in the flow guiding bush, the front end of the flame tube is connected with the spray nozzle, and an inlet of the transition section is connected with the rear end of the flame tube; an output guide vane is arranged in an output of the transition section, the transition section and the output guide vane are of an integrated structure, and air distribution cavities are formed in the output guide vane and the end wall of the front edge of the output guide vane of the transition section. According to the combustion chamber of the gas turbine, disclosed by the invention, the cooling flow of the end wall of the front edge of a primary stationary blade is saved, and the overall efficiency is increased.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a combustion chamber of a gas turbine with a cooling structure at the integrated connection between a transition section and a turbine. Background technique [0002] The basic working process of a gas turbine is: the air entering the gas turbine is compressed by the compressor; it is mixed with fuel in the combustion chamber for combustion; the high-temperature and high-pressure gas at the outlet of the combustion chamber enters the turbine to drive the turbine to do work, and the temperature and pressure of the gas are in the turbine. Each stage of the stationary blade and moving blade is lowered step by step to convert part of the heat energy of the gas into mechanical energy, which drives the compressor to rotate, and the other part of the heat energy is converted into mechanical energy for power or power generation. [0003] Generally speaking, the middle and rear sectio...

AI Technical Summary

Problems solved by technology

However, the distance between the installation edge after the transition section and the leading edge end wall of the first stage turbine vane is relatively large, and the cooling effect is limited. In order to achieve the required cooling effect, it is necessary to allocate more to the installation edge after the transition section than for the cooling itself required by the installation edge after the transition section Air, this part of the air cannot participate in combustion, which reduces the overall efficiency of the gas turbine

Another measure is to shorten the distance between the rear mounting edge of the transition section and the leading edge end wall of the turbine's first-stage vane, but this will have an adverse effect on the sealing of the rear installation edge of the transition section, and the damage caused by the turbine's first-stage vane The bow wave will have a great impact on the cooling of the rear mounting edge seal, resulting in shortened life of the seal structure or failure

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