Closed steam cooling blade for turbine of gas turbine

Abstract

A closed steam cooling blade for a turbine of a gas turbine, belonging to the technical field of blades for gas turbines. The closed steam cooling blade comprises an upper edge plate; a steam input pipeline I, a steam input pipeline II, a steam output pipeline I and a steam output pipeline II are arranged on the upper edge plate; a flow guide groove is formed in the upper tail edge side of a lower edge plate; an inserting piece is mounted in a blade body; a plurality of impact holes are formed in the front portion, right facing the inner side of the front edge of the blade body, of the inserting piece in the radial direction; an inner cavity of the inserting piece communicates with the steam input pipeline I; a plurality of partition plates arranged at equal intervals in the radial direction are arranged on the rear portion of a cooling cavity of the blade body and located on the rear portion of the inserting piece; a plurality of radial cooling channels are formed in the solid part of the tail edge of the blade body; the radial cooling channels penetrate through the whole blade tail from top to bottom; and the plurality of radial cooling channels communicate with one another through the flow guide groove formed in the lower edge plate. The negative influence caused by mixing of high-pressure air extracted from a gas compressor and a cooling medium with main runner gas is avoided, the cooling structure of the inner cavity of the blade is simplified, and the manufacturing cost of the blade is reduced.

Description

technical field [0001] The invention belongs to the technical field of gas turbine blades, and in particular relates to a gas turbine turbine closed steam cooling blade. Background technique [0002] An important way to improve the thermal efficiency of a gas turbine is to increase the inlet temperature of the turbine, but this makes the working environment of the turbine components worse, and the requirements for the performance of the materials are increasing day by day. At present, foreign countries have successfully developed gas turbines with an initial gas temperature above 1600°C and put them into practical use. Since the current high-temperature materials used in turbine blades can withstand a temperature of no more than 1000°C, reliable cooling measures must be taken for the high-temperature components of the gas turbine, especially the turbine blades, to reduce their operating temperature, so as to ensure the safe operation of the gas turbine . The cooling techno...

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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