A closed steam cooling blade of a gas turbine turbine

Abstract

A gas turbine turbine closed steam cooling blade, which belongs to the technical field of gas turbine blades, includes an upper edge plate, which is provided with a steam input pipe I, a steam input pipe II, a steam output pipe I and a steam output pipe II. The upper trailing edge side of the edge plate is provided with diversion grooves, inserts are installed in the blade body, and the front part of the insert facing the inner side of the leading edge of the blade body is provided with a plurality of impact holes in the radial direction, and the inner cavity of the insert is connected with the steam input pipe I. The rear part of the cooling cavity of the blade body is provided with a number of baffles arranged at equal intervals along the radial direction, and the baffles are located at the rear of the insert. The solid part of the blade body trailing edge is provided with a plurality of radial cooling channels, and the radial cooling channels are from top to bottom. The bottom runs through the entire tail of the blade, and multiple radial cooling passages are communicated through the guide grooves provided on the lower edge plate. It solves the negative impacts caused by the extraction of high-pressure air from the compressor and the mixing of the cooling medium and the gas in the main channel, simplifies the cooling structure of the inner cavity of the blade, and reduces the manufacturing cost of the blade.

Description

Technical field [0001] The present invention belongs to the field of gas turbine blades, and more particularly to a gas turbine transparent steam cooling blade. Background technique [0002] An important way to improve the thermal efficiency of gas turbines is to increase the turbine import temperature, but this has caused the working environment of the turbine to deteriorate, and the performance requirements of the material are increasing. At present, the gas turbine of 1,600 ° C above gas in the initial temperature of 1600 ° C has been developed abroad and is actually used. Since the temperature of the high-temperature material used in the current turbine blade does not exceed 1000 ° C, a high temperature component of the gas turbine, in particular the turbine blade, a reliable cooling measures must be taken to reduce its operating temperature, thereby ensuring the safe operation of gas turbine . Development and application of air as a cooling technique of cooling medium for de...

AI Technical Summary

Problems solved by technology

With the continuous increase of the turbine inlet temperature of the gas turbine, the amount of cooling air required is also increasing, and the amount of cooling air extracted by the ground gas turbine has reached more than 5%, which will have a very negative impact on the overall performance of the engine. The compressed air cannot participate in combustion, so it cannot become gas to do work on the turbine; the cooling air will eventually be discharged into the main gas flow, which will cause the temperature of the gas to drop, thereby reducing the output and efficiency of the turbine

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