Method for predicting temperature range of high-temperature alloy coating of segment of blading of gas turbine

A technology for high-temperature alloys and turbine blades, which is applied in the field of prediction of the life of high-temperature alloy coatings, and can solve problems such as oxidation failure of high-temperature alloy coatings

Active Publication Date: 2012-11-21
BEIJING HUAQING GAS TURBINE & INTEGRATED GASIFICATION COMBINED CYCLE ENG TECH
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Problems solved by technology

[0005] The purpose of the present invention is to provide a method for predicting the service temperature of the superalloy coating on the turbine blade of a gas turbine, to solve the problem of monitoring the oxidation failure of the superalloy coating th...

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  • Method for predicting temperature range of high-temperature alloy coating of segment of blading of gas turbine
  • Method for predicting temperature range of high-temperature alloy coating of segment of blading of gas turbine
  • Method for predicting temperature range of high-temperature alloy coating of segment of blading of gas turbine

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Embodiment l

[0035] The operating history of the blade Bucket1, the total operating time is more than 30,500 hours, the heavy oil operation is more than 25,000 hours, the coating is repaired after 24,000 hours, the ignition is started 1,798 times, the blade is removed after service, and the surface is inspected macroscopically. Serious fouling was formed. After cleaning, it was found that there were ablation marks on the trailing edge of 50% to 60% of the blade body. In order to further analyze the structural changes of the coating and predict the temperature, destructive testing was carried out.

[0036] In order to protect the original appearance of the superalloy coating from being destroyed during the preparation process, the coating is protected by a mild electroless nickel plating method. After the nickel plating layer is deposited on the surface, the sample is hot-mounted, and the sample is polished, dried and carbon-sprayed after preparation. processing, backscattering observation o...

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Abstract

A method for predicting temperature range of a high-temperature alloy coating of a segment of blading of a gas turbine belongs to the technical fields of service life prediction of hot parts of gas turbine and service state monitoring of surface coating. According to the invention, experiments and numerical calculation are combined to determine tissue change of the coating, so as to obtain a size L of an internal diffusion tissue in the coating; the L is substituted into a life prediction calculation model to predict a temperature, so as to carrying out temperature prediction on surface coating of the segment of blading of the gas turbine after service; meanwhile, temperature of the high temperature alloy matrix material is calculated out according to an aerodynamic heat value, a transfer value and a strength value; and a coating calculation temperature is obtained by temperature correction, and is then compared with an experimental temperature of the coating, so as to obtain a coating temperature closer to an actual working environment, and provide temperature parameters for further life prediction.

Description

technical field [0001] The invention relates to a method for predicting the service life of a high-temperature alloy coating of a hot end part of a gas turbine, in particular to an operation and processing method for temperature prediction. Background technique [0002] The moving blades of the turbine blades of gas turbines are made of Ni-based superalloys, and anti-oxidation and anti-corrosion coatings are used on the moving blades of the E-class and F-class units manufactured by several major gas turbine manufacturers. The coating is mainly MCrAlY high-temperature anti-oxidation bonding layer, which plays the role of anti-oxidation and anti-corrosion. As the inlet temperature of the gas turbine unit rises, the surface of the turbine blade will also be coated with YSZ (yttria stabilized zirconia) coating, which plays a role Due to the effect of insulating temperature, the coating in some units will also be coated with an aluminized layer to improve the oxidation resistance...

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Application Information

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IPC IPC(8): G01N25/20
Inventor 段方苗
Owner BEIJING HUAQING GAS TURBINE & INTEGRATED GASIFICATION COMBINED CYCLE ENG TECH
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