Composite cooling structure for turbine stator blade of gas turbine

Abstract

The invention relates to a gas turbine stator blade cooling system, in particular to a gas turbine stator blade composite cooling structure which comprises a stator blade, and four hollow inner cavities are formed in the stator blade. The hollow inner cavity close to the front edge of the stator blade is a first inner cavity, the hollow inner cavity close to the tail edge of the stator blade is a fourth inner cavity, a first insertion core is arranged in the first inner cavity, and a fourth insertion core is arranged in the fourth inner cavity; the first insertion core is of a thin-wall annular structure with two open ends, and the cross section of the first insertion core is of an open structure; a radial distance is reserved between the first insertion core and the inner wall of the stationary blade; a plurality of air holes are formed in the surface of the insertion core; a plurality of rows of air film holes are formed in the side wall of the static blade. The insertion core is processed and manufactured by adopting a mature stamping process, so that the manufacturing difficulty and the processing cost are reduced; and meanwhile, the overall temperature uniformity of the blade is improved, thermal stress is reduced, the failure probability of the tail edge of the stator blade is reduced, and the service life of the blade is prolonged.

Description

technical field [0001] The invention relates to a cooling system for a gas turbine stator blade, in particular to a composite cooling structure for a gas turbine turbine stator blade. Background technique [0002] From the simple cycle of the gas turbine, it can be seen that the specific power and performance of the gas turbine can be improved by increasing the initial gas temperature at the turbine inlet. The temperature around the turbine stator blades is high and the environment is harsh. The initial gas temperature of the F-class gas turbine is about 1400°C, which has far exceeded the tolerance limit of the metal of the stator blades. Therefore, the advanced cooling structure design of turbine stator blades is very important for the safe operation of gas turbines. [0003] At present, the turbine stator blades of gas turbines generally adopt a hollow structure, and cooling air is passed through the interior to take away the heat of the stator blades. The more common co...

AI Technical Summary

Problems solved by technology

[0006] First, the structure design of the diversion tube is complex and difficult to manufacture

Because the shape of the guide tube is generally consistent with the shape of the inner cavity of the stator blade, it is an irregular three-dimensional curved surface, and it is formed by stamping. Die design and manufacture are relatively difficult, resulting in low processing yield and high cost

[0007] Second, the thermal stress concentration at the trailing edge of the stator blade

The cooling air at the trailing edge of the stationary blade comes from the outlet of the compressor. Compared with the gas temperature, the temperature is very low. It enters the trailing edge chamber and flows out from the slit after passing through the convective heat exchange between the trailing edge pillars and ribs. Temperature, the temperature uniformity of the entire blade is poor, resulting in the concentration of thermal stress on the trailing edge of the stator blade, making the trailing edge of the stator blade a failure concentration point of the stator blade, reducing the service life of the stator blade

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