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Calibration method for measuring accuracy of high-temperature crack length through direct current potential method

A technology of crack length and direct current potential, which is applied in the direction of measuring devices, electric devices, electromagnetic means, etc., can solve the problems of crack length inaccuracy, sample surface oxidation, blackening, etc., and achieve the effect of convenient operation and strong practicability

Active Publication Date: 2015-06-03
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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Problems solved by technology

However, the main and a large number of tests of aero-engine materials are carried out under high temperature conditions. At high temperatures, the surface of the sample is oxidized and blackened, and the crack length cannot be observed visually.

Method used

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  • Calibration method for measuring accuracy of high-temperature crack length through direct current potential method
  • Calibration method for measuring accuracy of high-temperature crack length through direct current potential method
  • Calibration method for measuring accuracy of high-temperature crack length through direct current potential method

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Embodiment Construction

[0027] The present invention will be described in further detail below in conjunction with accompanying drawing and embodiment:

[0028] See attached Figure 1~3 As shown, this kind of calibration method for measuring the precision of high-temperature crack length by DC potentiometric method is characterized in that: the steps of the method are as follows:

[0029] Step 1. Referring to the requirements of the navigation mark HB7680-2000, process a compact tensile calibration sample 11. The material grade of this sample is a nickel-based superalloy of GH4169G. The width W of the sample is 40 mm, and the thickness B of the sample is Mark a current input solder joint position 3 on the sample width surface 2 on both sides of the notch 1 of the calibration sample 11, and the current input solder joint position 3 is in the center of the sample width W and sample thickness B, namely The position of the current input solder joint (3) is 20mm and 5mm from the edge of the sample width ...

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Abstract

The invention relates to a calibration method for measuring the accuracy of high-temperature crack length through a direct current potential method. The method uses a thread hooking method and the direct current potential method to measure the crack length of a high-temperature alloy specimen. As the crack front at the fracture part of the specimen is arc-shaped, the intermediate crack length is the longest, and the crack length of the surface of the specimen is the shortest. The crack length measured by the potential method is compared with the average crack length, the surface crack length and the internal crack length measured through the thread hooking method, and the average crack length measured through the direct current potential measurement method is most consistent with the average crack length measured through the thread hooking method, so that the crack length can be calibrated through the thread hooking method.

Description

technical field [0001] The invention relates to a calibration method for measuring the length precision of a high-temperature crack by a direct current potential method, belonging to the technical field of test and test. Background technique [0002] Metal structural materials are prone to fatigue fracture problems under cyclic loading. The fatigue crack growth resistance of materials is an important performance index that must be considered in the damage tolerance design of aircraft and engines. High-temperature alloys have high high-temperature strength, good creep resistance and fatigue resistance, and high oxidation resistance and thermal corrosion resistance. They are widely used in aerospace engines, railway locomotives and other key high-temperature components of industries. Material. Crack length is the basis of crack growth performance data, and its measurement results will directly affect the results of aircraft and engine damage tolerance design. [0003] In th...

Claims

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Application Information

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IPC IPC(8): G01B7/02
Inventor 王亮黄新跃郭广平
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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