Surface wave in-situ flaw detection method of rotor blade with coating

A technology of rotor blades and surface waves, which is applied to the analysis of solids using sound waves/ultrasonic waves/infrasonic waves, can solve problems such as difficult detection, large curvature of the blade tenon, complex structure, etc., to overcome the difference in detection sensitivity, improve discovery capabilities, and avoid air crashes The effect of the accident

Inactive Publication Date: 2013-04-24
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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AI Technical Summary

Problems solved by technology

[0003] Since the material of the rotor blade is martensitic stainless steel with a non-metallic coating on the surface, and the curvature

Method used

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  • Surface wave in-situ flaw detection method of rotor blade with coating
  • Surface wave in-situ flaw detection method of rotor blade with coating

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Embodiment Construction

[0027] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0028] A surface wave in-situ flaw detection method for coated rotor blades, the flaw detection method uses a surface wave probe with a frequency of 2.5MHz and a chip size of 6×7mm, and a digital ultrasonic flaw detector model KW-4C, specifically including Follow the steps below:

[0029] Step 1: Turn on the ultrasonic flaw detector, preheat it for 10 minutes, and connect the surface wave probe to the ultrasonic flaw detector through the cable;

[0030] Step 2: Set the parameters of the ultrasonic flaw detector, set the surface wave probe frequency, chip size, impedance size, display mode, etc.;

[0031] Step 3: Place the positioning jig on the blade comparison test piece with artificial damage, make the slot of the positioning jig parallel to the edge of the blade tenon of the blade comparison test piece, and clamp it tightly; Appl...

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Abstract

The invention relates to a surface wave in-situ flaw detection method of a rotor blade with a coating. The invention belongs to the technical field of aircraft engine, and is mainly used in surface wave in-situ detection of aircraft engine rotor blades with coatings. With the method provided by the invention, coating thickness influence can be sufficiently excluded, and discovery capability of tiny defects on blade surface and near-surface can be improved. The method comprises the steps that: an ultrasonic flaw detector is started, and a surface wave probe is connected to the ultrasonic flaw detector; a positioning fixture is placed on a blade contrast sample with artificial flaw, and sensitivity is checked; the positioning fixture is fetched from the blade contrast sample, and is placed on a blade requiring flaw detection; the surface wave probe is moved from outside to inside along a slot of the positioning fixture, and is swung left and right, until the probe reaches a slot limit end, such that blade scanning is finished; when blade scanning is finished, the positioning fixture is removed, and an coupling agent on the blade is wiped off; and the other blades are scanned one by one with the same method.

Description

technical field [0001] The invention belongs to the technical field of aero-engines, and in particular relates to a surface wave in-situ flaw detection method for coated rotor blades, which is mainly applied to the in-situ surface wave detection for aero-engine coated rotor blades. Background technique [0002] The I-stage rotor blades of the low-pressure compressor of the aero-engine are located at the outermost part of the engine compressor. During the high-speed rotation of the engine, they are subjected to large vibration stress, centrifugal force and high-temperature gas erosion and corrosion. ) are prone to fatigue cracks. During the use of the engine, the compressor blades are prone to broken faults, and the broken compressor blades are easy to damage some parts on the engine, causing heavy losses. Therefore, there is an urgent need to study a detection method for blade inspection before engine operation, and remove blades with hidden cracks. [0003] Since the mate...

Claims

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Application Information

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IPC IPC(8): G01N29/04
Inventor 张传明董德秀朱萍赵帅军
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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