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Engine blade in-situ ultrasonic detection method

A technology for engine blades and ultrasonic testing, which is applied to the analysis of solids using sound waves/ultrasonic waves/infrasonic waves, material analysis using sound waves/ultrasonic waves/infrasonic waves, and measuring devices, which can solve problems such as long cycle times and high costs

Active Publication Date: 2013-03-27
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the process of returning the engine to the factory, disassembling, inspecting, assembling, testing, and qualified delivery is not only long-term, but also expensive, so this solution is not suitable

Method used

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  • Engine blade in-situ ultrasonic detection method
  • Engine blade in-situ ultrasonic detection method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0047]An in-situ ultrasonic detection method for engine blades. First, a special ultrasonic detection probe is made, and then the probe is used to verify the sensitivity and effectiveness of the detection device on a reference standard with artificial damage, and then the ultrasonic detection probe is put into the engine. Check the position for in-situ testing.

[0048] The in-situ ultrasonic detection method of the engine blade requires: use a special probe to perform in-situ detection in the outer field of the engine blade, obtain an A-scan waveform diagram on the ultrasonic flaw detector, and then determine the detected defects in the probe scanning area according to the A-scan waveform diagram. Whether the leaves are damaged;

[0049] The special-purpose probe is specifically composed of the following structures: probe body 1, socket 2, water pipe 3, cable 4, piezoelectric chip 5; wherein: probe body 1 and socket 2 are fixedly connected as one; water pipe 3 and The cables...

Embodiment 2

[0093] This embodiment is basically the same as Embodiment 1, and its main differences are:

[0094] 1) The special probe meets the following requirements: it is a shaft-shaped or rod-shaped component as a whole, and the maximum diameter of the outer contour of the cross-section or the diameter of the circumscribed circle of the cross-section is required to be ≤ 8mm. The diameter of the round hole at the casing where the probe may protrude into the engine corresponds to this requirement. ,

[0095] 2) In the in-situ ultrasonic testing method for engine blades, the cross-sectional outer contour of the probe body 1 of the special probe is circular, and at the same time, the distance between the outer end surface of the probe body 1 facing the side of the detected object and the axis of the probe body 1 is There is an included angle of 12°.

[0096]

Embodiment 3

[0098] This embodiment is basically the same as Embodiment 1, and its main differences are:

[0099] 1) The special probe meets the following requirements: it is a shaft-shaped or rod-shaped component as a whole, and the maximum diameter of the outer contour of the cross-section or the diameter of the circumscribed circle of the cross-section is required to be ≤10mm. The diameter of the round hole at the casing where the probe may protrude into the engine corresponds to this requirement. ,

[0100] 2) In the in-situ ultrasonic testing method for engine blades, the cross-sectional outer contour of the probe body 1 of the special probe is circular, and at the same time, the distance between the outer end surface of the probe body 1 facing the side of the detected object and the axis of the probe body 1 is There is an included angle of 16°.

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Abstract

An engine blade in-situ ultrasonic detection method comprises the following steps: carrying out in-situ detection of an engine blade in the outfield through using a special probe to obtain an A scanning oscillogram on an ultrasonic flaw detector, and determining whether the detected blade in the scanning area of the probe is damaged or not according to the A scanning oscillogram, wherein the special probe concretely comprises a probe body (1), a plug seat (2), a water tube (3), a cable (4) connected with the ultrasonic flaw detector, and a piezoelectric wafer (5). The method realizes the in-situ detection, and has a very prominent economic value, a huge technological application value and excellent technological effects.

Description

technical field [0001] The invention relates to the technical background of the in-situ ultrasonic detection of the first-stage rotor blades of a high-pressure compressor of an aeroengine, and in particular provides an in-situ ultrasonic detection method of the engine blades. Background technique [0002] During the use of the first-stage rotor blade of the high-pressure compressor of an engine, cracks occurred at the angle R of the tenon pressure surface on the exhaust side. In order to ensure the safety of flying in the field, it is urgent to study effective and reliable non-destructive testing methods for in-situ inspection. It is known from relevant information that civil aviation IAE company V2500 A5 / D5 series engines have found cracks on the tenon pressure surface of the fourth-stage rotor blade of the high-pressure compressor; obviously, such incidents have seriously affected the flight safety of the aircraft. If the engine is returned to the factory for maintenance,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N29/04G01N29/24
Inventor 熊瑛董德秀段建刚朱萍赵茂旭
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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