Trailing edge slit cooling structure and method applicable to turbine blade, turbine blade

Abstract

The invention provides a trailing edge split cooling structure suitable for turbine blades, comprising a partition rib, a blade trailing edge split and a wall surface depression group, wherein the partition ribs are arranged on the wall surface of the blade trailing edge split; two partition ribs The space between forms the blade trailing edge slit; the wall surface of the blade trailing edge slit is arranged with a wall surface depression group; the wall surface depression group includes a plurality of wall surface depressions, the wall surface depression group includes a plurality of wall surface depressions, and the extension direction of at least one wall surface depression Form an inclined angle with the partition rib; and / or, the extension direction of at least one wall surface recess forms an inclined angle with the other side of the partition rib; when the cold airflow enters the trailing edge of the turbine blade, it flows through the wall surface depression along the cold air flow direction through the pin fin A helical vortex is generated which is directed to the partition ribs on both sides. The invention can enhance the cooling performance of the trailing edge slit of the turbine blade and improve the external air film cooling performance by arranging the wall surface depression on the blade trailing edge slit, and is beneficial to reduce the consumption of tail cooling air.

Description

technical field [0001] The invention relates to the technical field of turbine blade cooling, in particular to a trailing edge slit cooling structure and method suitable for a turbine blade, and a turbine blade. Background technique [0002] The trailing edge of the turbine blade of the existing aero-engine and gas turbine adopts a split-jet air-film cooling structure. The cooling channel inside the trailing edge of the turbine blade is composed of the pressure side wall and the suction side wall of the turbine blade, as well as the partition rib, and the partition rib is the extension of the pressure side wall on the split wall of the trailing edge. [0003] The slit at the trailing edge of the turbine blade is a difficult part to cool. Since the design of the turbine blade requires high aerodynamic efficiency, the trailing edge of the turbine blade must be very thin, which makes it difficult to arrange a complex internal cooling structure inside the narrow tail of the turb...

AI Technical Summary

Problems solved by technology

Although this prior art can form a uniform cooling air film on the surface of the blade during initial cooling, the flow of the air film on the surface of the trailing edge slit will still be easily disturbed by the shear flow and eddy current as it is used, resulting in obvious Flow separation leads to a decrease in the air film cooling performance on the surface of the slit, which increases the temperature of the slit wall and causes ablation, shortening the working life of the turbine blades

In addition, in this solution, ribs are arranged on the split surface of the trailing edge, which increases the weight of the blade and also increases the aerodynamic loss of the external mainstream of the blade, which will reduce the performance of the turbine engine

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