Turbine rotor blade of gas turbine

Abstract

The invention discloses a turbine rotor blade of a gas turbine. The turbine rotor blade comprises a blade root, a blade platform and a blade profile, wherein a cooling structure of a snakelike passage is adopted in the blade, and comprises three cooling loops for circulating cooling gas, namely an impingement cooling loop for cooling a front edge region of the blade, a strengthening convection cooling loop for cooling a top region of the blade and a column rib and jet cooling loop for cooling a tailing edge region of the blade. For the cooling gas flowing to the tailing edge of the blade, at least one flow guide sheet structure is added at an elbow region close to the tailing edge of the blade and the blade root, so that sufficient cooling gas is distributed for cooling the root of the tailing edge of the blade. Thus, the temperature of the root of the tailing edge of the blade is reduced.

Description

technical field [0001] The invention relates to a turbine rotor blade of a gas turbine, in particular to a rotor blade with a plurality of cooling circuits to strengthen the cooling effect of the root of the trailing edge of the blade profile. Background technique [0002] With the continuous increase of the inlet gas temperature of the gas turbine turbine, the heat load environment faced by the high temperature components of the turbine is getting worse. In order to ensure a reasonable service life of the high-temperature turbine blades, it needs to be effectively cooled, among which, the cooling form of the high-temperature turbine rotor blades is the most complicated. At present, the most advanced turbine rotor blades in the world adopt the form of multiple cooling circuits and serpentine channels to enhance convective cooling, so as to keep the temperature field and stress distribution of the blade body at a reasonable level. [0003] Due to the structural characteristi...

AI Technical Summary

Problems solved by technology

On the one hand, due to the geometric characteristics of the elbow, it is difficult for the cooling gas to enter the injection hole in the root area of ​​the trailing edge after passing through the elbow, and the effect of centrifugal force intensifies this effect. There is less cooling gas in the root area of ​​the trailing edge of the blade, resulting in poor cooling effect in the root area of ​​the trailing edge of the blade, and its temperature and thermal stress are greater

Under the influence of the above two factors, the root area of ​​the trailing edge of the turbine rotor blade is extremely prone to high-temperature oxidation due to excessive temperature or excessive thermal stress, and failure phenomena such as cracks and even ablation occur.

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