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An experimental evaluation method for the service temperature of superalloy turbine blades

A technology of service temperature and turbine blades, which is applied in the direction of measuring devices, instruments, scientific instruments, etc., can solve problems such as quantitative evaluation of degraded tissue, achieve strong engineering application significance and broad prospects, eliminate complex influences, and reliable evaluation results Effect

Active Publication Date: 2018-08-03
UNIV OF SCI & TECH BEIJING
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Problems solved by technology

Due to the different working conditions of different parts of the blade, there are differences in the degradation degree of the microstructure after service. By quantifying and characterizing the degradation degree of the microstructure of the blade after service, the service environment of the blade can be indirectly deduced, so that the degraded microstructure can be used to evaluate the service temperature field of the blade. It is possible, but there is no relevant report on quantifying the degraded tissue and using it to quantitatively evaluate the actual service temperature of the blade

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  • An experimental evaluation method for the service temperature of superalloy turbine blades
  • An experimental evaluation method for the service temperature of superalloy turbine blades
  • An experimental evaluation method for the service temperature of superalloy turbine blades

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Embodiment Construction

[0020] The following examples will further illustrate the present invention so that those skilled in the art can better understand the advantages and features of the present invention.

[0021] First, verify whether the original structure of the DZ125 service blade and sheet material DZ125 alloy is similar or consistent. Observing the microstructure of the tenon part of the DZ125 alloy blade and the blade material DZ125 alloy after standard heat treatment, the morphology, size and cubic degree of the γ'phase of the two are very close, respectively. figure 1 and figure 2 Shown. Refer to the grid number point method in GB / T 15749 to quantify the volume fraction of γ'phase. Set 216 grid intersection points. When the intersection point is in the γ'phase, it is counted as 1, when the intersection point is in the γ'phase and the substrate interface, it is counted as 0.5, and when the intersection point is in the matrix, it is counted as 0. The ratio of the above statistical results to...

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Abstract

The invention provides an experiment assessment method of the service temperature of a high temperature alloy turbine blade, and relates to experiment assessment of the service temperature of a DZ125 directional solidification high temperature alloy turbine blade. A corresponding relationship among the temperature, the time and the volume fraction of a primary gamma' phase in dendrite arm is determined through blade material laboratory heat exposure experiments according to a thermodynamic phase equilibrium principle. The substrate temperature of the service blade is assessed by using the relationship and the volume fraction of the primary gamma' phase of the blade after practical service for a period of time. The method eliminates complex influences of blade coating and gas film cooling on the service temperature of the blade, is reliable in assessment of the service temperature of the blade substrate, is suitable for being applied in engineering, and has strong engineering application values and wide prospect in the service temperature assessment of the DZ125 blade.

Description

Technical field [0001] The invention belongs to the technical field of nickel-based directionally solidified superalloy blades, and in particular relates to an experimental evaluation method for the service temperature of a directionally solidified turbine blade. Background technique [0002] Aeroengines are highly complex and precise thermal machinery. As one of the most critical components of aeroengines, turbine blades are important hot-end components that convert the enthalpy and kinetic energy of gas into mechanical energy. With the continuous improvement of the thrust-to-weight ratio of aero-engines, the temperature of the external gas of the blades continues to increase, often far exceeding the melting point of the blade material. Therefore, it is necessary to use coatings, surface film cooling, internal cooling holes, etc. to reduce the blade base temperature, but also The substrate temperature measurement and calculation increase the difficulty. At the same time, due to...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N17/00
CPCG01N17/006
Inventor 冯强陈亚东安文瑞郑运荣
Owner UNIV OF SCI & TECH BEIJING
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