Turbine blade-wheel disc combined cooling structure of gas turbine

Abstract

The invention relates to a turbine blade-wheel disc combined cooling structure of a gas turbine. The turbine blade-wheel disc combined cooling structure of the gas turbine comprises a rotating shaft, a front-stage wheel disc, a front-stage moving blade, a wheel disc front cover plate, a wheel disc rear cover plate, end face teeth and the like. The wheel disc front cover plate and the wheel disc rear cover plate are installed on the two sides of the front-stage wheel disc; the wheel disc rear cover plate is connected with the front-stage wheel disc and a rear-stage wheel disc through end face teeth; a cooling airflow channel is formed in the rotating shaft, and a wheel disc center cooling cavity is formed between the front-stage wheel disc and the rear-stage wheel disc; the wheel disc rear cover plate is provided with a plurality of end face holes, a plurality of injection holes, a balance block and sealing teeth; the sealing teeth and a rear-stage stationary blade platform form a sealing structure; a wheel disc middle cooling cavity and a wheel flange-blade root cooling cavity are formed in the middle and the wheel flange of the wheel disc rear cover plate and the front-stage wheel disc; and a blade root internal cooling channel is formed in the blade root of the front-stage moving blade, and the front-stage moving blade is provided with an internal cooling channel and a trailing edge crack. According to the turbine blade-wheel disc combined cooling structure of the gas turbine provided by the invention the cold source characteristic of a cooling airflow is fully utilized to perform combined cooling on all parts, so that the cooling airflow loss is small, and the cooling pipeline arrangement is simple.

Description

technical field [0001] The invention belongs to the field of gas turbines, and in particular relates to a turbine blade-disc joint cooling structure of a gas turbine. Background technique [0002] With the continuous development of gas turbines, the inlet temperature of the turbine continues to increase, and the temperature load on each component is also increasing. Blades and discs are the key components of gas turbines. They are not only affected by high temperature loads in the flow area, but also by high-speed centrifugal loads, and the force is very complicated. In order to reduce the impact of high temperature stress on the service life of blades and discs, it is necessary to cool the blades and discs to ensure the safe operation of the gas turbine. At present, engineering usually introduces two streams of low-temperature cooling gas from the compressor stage to perform convective heat exchange on the inside of the blade and the surface of the disk respectively, so as...

AI Technical Summary

Problems solved by technology

However, the temperature of the cooled gas is low, and when mixed with the high-temperature mainstream gas, the temperature of the mainstream gas will be lowered, which will affect the performance of the gas turbine.

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