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A closed steam cooling blade of a gas turbine turbine

A gas turbine, steam cooling technology, applied in the direction of blade support components, mechanical equipment, engine components, etc., can solve the problems of gas temperature reduction, reduce turbine output and efficiency, etc., to improve gas turbine efficiency and output power, reduce manufacturing cost effect

Active Publication Date: 2022-03-01
中国航发燃气轮机有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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  • A closed steam cooling blade of a gas turbine turbine
  • A closed steam cooling blade of a gas turbine turbine
  • A closed steam cooling blade of a gas turbine turbine

Examples

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Embodiment Construction

[0019] The present invention is further detailed below with reference to the accompanying drawings and examples.

[0020] Such as Figure 1 to 8 As shown, a gas turbine turntable steam cooling blade includes a blade body, an upper edge plate 5, a lower edge plate 6, a steam input conduit I1, a steam input conduit II2, a steam output conduit I3 and a steam output conduit II4, said A steam input conduit I1, steam input conduit II2, steam output conduit I3 and steam output conduit II4 are provided on the upper edge plate 5, and the upper tap side of the lower edge plate 6 is provided with a guide groove 7, and the blade body is mounted. The insert 10 is spaced apart from the front portion of the insert 10 on the inside of the front edge of the blade body, and the inner cavity of the insert 10 is in communication with the steam input pipe I1, via the impact hole 8 pairs of blades In the front edge of the body, the cooled steam flows along the pressure side and the suction side space fo...

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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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
CPCF01D5/18F01D5/187
Inventor 权立宝潘春霖郑伟李小萌郭振轩
Owner 中国航发燃气轮机有限公司
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