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A Method of Measuring Turbine Blade Temperature Based on Flame Spraying

A turbine blade and flame spraying technology, applied in the field of aviation testing, can solve the problems of low turbine blade test accuracy, large damage to the turbine blade structure, and inability to accurately measure real-time monitoring, achieving significant military, real-time monitoring and measurement, and flow field interference small effect

Active Publication Date: 2018-10-12
AECC SICHUAN GAS TURBINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Purpose of the present invention: In order to solve the problem of low test accuracy of turbine blades, large damage to turbine blade structure, incapable of accurate measurement and real-time monitoring

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0012] The present invention will be described in further detail below by means of specific embodiments:

[0013] The invention is a method for measuring the temperature of a turbine blade based on flame spraying. Firstly, the surface of the turbine blade is pretreated to remove various foreign matter on the surface of the blade and provide a good base suitable for painting requirements. Next, the flame spraying process is used to complete the preparation of the insulating coating. After that, the selection of measuring points and the installation and fixing of the micro thermocouples are completed. Finally, the high-temperature insulating coating is sprayed again to complete the protection of the temperature measurement function layer.

[0014] The method for measuring the temperature of the turbine blade based on flame spraying includes pretreatment of the surface of the turbine blade, preparation of an insulating layer, preparation of a functional layer, preparation of a pro...

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PUM

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Abstract

The invention belongs to the technical field of aviation testing, and in particular relates to a micro thermocouple fixed on a metal surface with a high-temperature insulating coating, which is an expansion of the thermocouple testing technology. In the present invention, the high-temperature-resistant insulating material Al2O3 ceramic rod is melted and sprayed onto the base body of the turbine blade through surface treatment and flame spraying of the turbine blade, so that a firm metallurgical bond is formed between the coating and the base body of the turbine blade, and then the fine thermocouple is fixed on the insulating coating. The measuring end of the micro-thermocouple is fixed on the surface of the substrate by parallel welding or spherical welding, and then through the flexible lead technology, the signal transmission and acquisition are completed. The invention fixes the micro thermocouple based on the high-temperature insulating coating, and accurately measures the surface temperature of the turbine rotor blade by using the micro thermocouple.

Description

technical field [0001] The invention belongs to the technical field of aviation testing, in particular to a method for measuring the temperature of a turbine blade based on flame spraying. Background technique [0002] The turbine is one of the three key components of an aero-engine. In order to improve the thrust-to-weight ratio, an important technical approach is to increase the turbine inlet temperature, which will inevitably lead to higher and higher turbine temperatures, causing the turbine blades to bear a huge heat load, and the turbine rotor blades are still rotating at high speed in the hot high-temperature and high-pressure gas flow. The turbine blades will be subject to severe thermal stress and strain, therefore, the thermal load on the turbine blades is one of the important factors for blade ablation and fracture. Measuring the temperature of turbine blades and mastering the temperature distribution rules are important basis for analyzing the ablation fracture ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C4/129G01K7/04G01K1/14G01K1/143
CPCG01K1/143G01K7/04
Inventor 熊庆荣徐毅陈洪敏刘先富张文学熊兵程新琦
Owner AECC SICHUAN GAS TURBINE RES INST