Staggered cooling structure of flame tube in combustion chamber of gas turbine

Abstract

The invention discloses a staggered cooling structure of a flame tube in a combustion chamber of a gas turbine and belongs to the technical field of gas turbines. The cooling structure comprises a plurality of ring-shaped flow limiting plates which are arranged in the axial direction of the flame tube, wherein the outer sides of the ring-shaped flow limiting plates are fixed on the inner wall of a diversion lining; cooling holes which are rectangular or semicircular are formed in the inner sides of the ring-shaped flow limiting plates in the circumferential direction. The cooling holes are capable of enhancing the convective heat transfer coefficient, improving the cooling effect of the flame tube and preventing the temperature of the flame tube from getting too high. The ring-shaped flow limiting plates radially extend to the flame tube; the cooling holes of every two adjacent ring-shaped flow limiting plates are distributed in the circumferential direction in a staggered manner, so that the flowing of the air can be limited, the flowing time of the return air can be increased and benefit is brought to fully cool the flame tube. Through improving the cooling, the reliability of the flame tube is improved and benefit is brought to prolong the service life of the flame tube.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a cooling structure for a combustion chamber flame tube of a gas turbine. Background technique [0002] A gas turbine consists of three major components: a compressor, a combustor, and a turbine. Among them, the highest temperature zone of the gas turbine exists in the combustion chamber, which is used as a gas combustion component connecting the compressor and the turbine, converts chemical energy into heat energy, and passes hot air into the turbine to perform work. A fuel nozzle is installed at the front end of the combustion chamber. The fuel ejected from the nozzle and the incoming air are combusted in the combustion chamber. The combustion temperature can reach more than 2000 degrees Celsius and the pressure can reach 20 atmospheres. It is difficult for the outer cylinder of the combustion chamber to withstand such high pressure at high temperature. In order to reduc...

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Problems solved by technology

[0005] On the one hand, the flame tube has been working at high temperature for a long time, facing creep and oxidation problems, and it suffers from thermomechanical fatigue during the continuous start-up and shutdown of the gas turbine; on the other hand, due to the uncertainty of the combustion field in the flame tube, The non-uniformity of the heat load and the limitation of the cooling performance of the traditional cooling structure lead to the uneven temperature distribution of the wall of the flame tube itself, which is easy to cause large thermal stress

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