High-temperature flame flow device for dynamically and cyclically testing thermal shock resistance of thermal barrier coating

A technology of thermal barrier coating and thermal shock resistance, which is applied in the direction of measuring devices, strength characteristics, instruments, etc., can solve the problems of small flame jet beam spot, large radial temperature gradient of flame flow, and weak heating capacity, etc. The effect of small temperature gradient and constant temperature field

Active Publication Date: 2014-01-01
SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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  • Abstract
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Problems solved by technology

Currently available information shows that several domestic scientific research institutes have built test devices using oxygen/coal gas or oxygen/acetylene flames as heat sources. The enthalpy values ​​of gas and acetylene gas flames are both low, and the heating capacity is not strong.

Method used

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  • High-temperature flame flow device for dynamically and cyclically testing thermal shock resistance of thermal barrier coating
  • High-temperature flame flow device for dynamically and cyclically testing thermal shock resistance of thermal barrier coating
  • High-temperature flame flow device for dynamically and cyclically testing thermal shock resistance of thermal barrier coating

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Embodiment Construction

[0036] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0037]The high-temperature flame flow device for testing the thermal shock resistance of thermal barrier coatings in a dynamic cycle of the present invention is suitable for testing the thermal shock resistance, which is an important performance index for measuring the service performance of thermal barrier coatings, in the field of aeroengines. figure 1 It is a structural schematic diagram of an embodiment of a high-temperature flame flow device for testing the thermal shock resistance performance of a thermal barrier coating in a dynamic cycle of the present invention. and image 3 It is a schematic cross-sectional view of a flame jet nozzle (hereinafter referred to as a flame nozzle) which is an embodiment of the high-temperature flame device according to the present invention.

[0038] The high-temperature flame flow device for d...

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Abstract

The invention relates to a high-temperature flame flow device for dynamically and cyclically testing thermal shock resistance of a thermal barrier coating. The high-temperature flame flow device comprises a rotatable sample mounting unit, a heating unit, a cooling unit and a control unit, wherein the sample mounting unit is used for mounting multiple samples; the heating unit is used for heating coated surfaces of the samples and is provided with at least one flame nozzle with multiple flame cores which are annularly arranged in a shape of a concentric circle; the cooling unit is used for cooling the samples; the control unit is configured to control rotation of the sample mounting unit, so that the multiple samples are alternately heated and cooled. According to the high-temperature flame flow device, a constant temperature field flame flow with a small radial temperature gradient can be formed, and the thermal shock resistance of the multiple samples can be dynamically and cyclically tested concurrently.

Description

technical field [0001] The invention relates to performance testing of thermal barrier coatings, in particular to a high-temperature flame flow device for dynamic cycle testing of thermal shock resistance of thermal barrier coatings. Background technique [0002] One of the important ways to improve the thermal efficiency of an aeroengine, especially an aerogas turbine engine, is to increase the gas temperature at the turbine inlet of the turbine engine. With the development of aero-engines towards a higher thrust-to-weight ratio, the gas temperature at the turbine inlet also continues to rise. Even under the premise of using high-efficiency film cooling technology, the operating temperature of the guide vanes of the high-pressure turbine exceeds the current maximum high-temperature performance. Excellent reliable service temperature for single crystal superalloy blades. Therefore, it has become one of the effective measures to solve this problem to use a thermal insulation...

Claims

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Application Information

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IPC IPC(8): G01N3/60
Inventor 钟兴华赵华玉陶顺衍周霞明杨凯刘晨光王亮丁传贤
Owner SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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