CN115372457A

CN115372457A - Comparison sample piece and method for detecting rotor blade by using same

Info

Publication number: CN115372457A
Application number: CN202211016762.1A
Authority: CN
Inventors: 陈登举; 杨晗; 王宏伟; 杨雅琨; 胡小康; 王勇; 杨佩
Original assignee: Haixiang Machinery Factory Yongnian District Handan City
Current assignee: Haixiang Machinery Factory Yongnian District Handan City
Priority date: 2022-08-24
Filing date: 2022-08-24
Publication date: 2022-11-22

Abstract

The invention discloses a comparison sample piece for a rotor blade and a method for detecting the rotor blade by using the comparison sample piece, wherein the comparison sample piece comprises a flange plate, a root part and a blade body, the flange plate is placed between the root part and the blade body for isolating the root part and the blade body, and the root part is positioned on one side of the flange plate and abuts against the flange plate; the root part is provided with a through hole which is positioned in the middle of the root part; the blade body is located the other side of rim plate and supports the rim plate, the blade body includes: the exhaust edge is positioned on the upper edge of the blade body; the air inlet edge is positioned at the lower edge of the blade body; and the two ends of the notch are respectively positioned at the positions of the air inlet edge and the air outlet edge at certain distances from the edge plate. The technical scheme of the invention can carry out flaw detection without damaging the surface anticorrosive coating, and has good economic benefit, good operability, high efficiency and high detection sensitivity.

Description

Comparison sample piece and method for detecting rotor blade by using same

Technical Field

The present invention relates generally to the field of aircraft engines, and more particularly to a comparison sample for a rotor blade and a method of inspecting a rotor blade using the comparison sample.

Background

If the 2 nd-4 th-stage rotor blade of the low-pressure compressor of the aircraft engine has blade fracture failure in the working process, parts such as the compressor, a combustion chamber, a turbine, a tail nozzle and the like can be damaged to different degrees. When the crack property of the blade is fatigue fracture, the fracture initiation location is typically the inlet and exhaust edges of the blade. Through investigation and analysis, during the manufacturing and processing of the blade, the air inlet and outlet edges of the blade are easy to have casting defects, namely stress concentration points are easy to generate during the working process, so that fatigue cracks are initiated. When the crack propagates to a certain extent, blade fatigue fracture occurs. Therefore, when the engine is repaired, defects and cracks on the air inlet and outlet edges of the blades can be timely found by carrying out flaw detection on the air inlet and outlet edges of the blades through eddy current detection.

Disclosure of Invention

In view of the above technical problem, the present disclosure proposes a comparison sample for a rotor blade, comprising: a platform, and a platform, wherein the platform is placed between the platform and the platform for isolating the platform from the platform, the platform being located on one side of the platform and abutting the platform; the root part is provided with a through hole which is positioned in the middle of the root part; the blade body is located the other side of rim plate and supports the rim plate, the blade body includes: the exhaust edge is positioned at the upper edge of the blade body; the air inlet edge is positioned at the lower edge of the blade body; and the two ends of the notch are respectively positioned on the air inlet edge and the air exhaust edge and are away from the edge plate by a certain distance.

In a preferred embodiment, the certain distance is 20mm.

In a preferred embodiment, the width of the notch is 0.13mm.

In a preferred embodiment, the depth of the score groove is 0.5mm.

In a preferred embodiment, the comparative sample is made of an aluminum alloy material.

In a preferred embodiment, the surface of the blade body is coated with ES205 enamel.

In another aspect, the present disclosure also provides a method of inspecting a rotor blade using a reference sample, including the steps of: s1, initializing an eddy current flaw detector; s2, debugging the eddy current flaw detector by using the comparison sample piece, so that when the eddy current flaw detector is used for detecting flaws of the comparison sample piece, the eddy current flaw detector can give an alarm to indicate that flaws are detected; s3, recording detection parameters of the eddy current flaw detector; s4, flaw detection is carried out on the rotor blade by using the eddy current flaw detector based on the recorded detection parameters; and S5, responding to the alarm of the eddy current flaw detector, and determining that the rotor blade has the defect.

In a preferred embodiment, the detection parameters include one or more of: frequency value, gain, phase, digital filter value, high pass filter frequency, low pass filter frequency, pre-gain, and drive value.

In a preferred embodiment, the frequency value is 476.2kHz, the gain is 35dB, the phase is 201DEG, the digital filter value is 4.0, the high pass filter frequency is 3.0Hz, the low pass filter frequency is 88.0Hz, the pre-gain is 25dB, and the drive value is 5.

In a preferred embodiment, the eddy current flaw detector is model number SMART5097.

Compared with the prior art, the beneficial effects of the disclosure are: the method can be used for carrying out flaw detection on the premise of not damaging the surface anticorrosive coating of the rotor blade of the low-pressure compressor of the engine, and has the advantages of good economic benefit, good operability, high efficiency and high detection sensitivity.

Drawings

The novel features of the invention are set forth with particularity in the appended claims. A better understanding of the features and advantages of the present invention will be obtained by reference to the following detailed description that sets forth illustrative embodiments, in which the principles of the invention are utilized, and the accompanying drawings. The drawings are only for purposes of illustrating embodiments and are not to be construed as limiting the invention. Also, in the drawings, wherein like reference numerals refer to like elements throughout:

FIG. 1 illustrates a schematic view of a comparison sample for a rotor blade according to an exemplary embodiment of the present disclosure; and

FIG. 2 illustrates a flow chart of a method of inspecting a rotor blade using the comparison sample according to an exemplary embodiment of the present disclosure.

Description of the reference numerals

1 root, 2 edge plates, 3 blade bodies, 4 exhaust edges, 5 air inlet edges and 6 notches.

Detailed Description

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. Nothing in the following detailed description is intended to indicate that any particular component, feature, or step is essential to the invention. Those skilled in the art will appreciate that various features or steps may be substituted for or combined with one another without departing from the scope of the present disclosure.

FIG. 1 illustrates a schematic view of a comparison sample for a rotor blade according to an exemplary embodiment of the present disclosure. The present disclosure presents a comparison sample for a rotor blade comprising: a root 1, a platform 2 and a blade 3, the platform 2 is placed between the root 1 and the blade 3 for isolating the root 1 and the blade 3, the root 1 is located at one side of the platform 2 and is abutted against the platform 2, the root 1 is provided with a through hole, and the through hole is located at the middle part of the root 1; the blade body 3 is located on the other side of the platform 2 and abuts against the platform 2, and the blade body 3 comprises: the exhaust edge 4 is positioned at the upper edge of the blade body 3; a gas inlet edge 5, wherein the gas inlet edge 5 is positioned at the lower edge of the blade body 3; and the two ends of the notch 6 are respectively positioned on the air inlet edge 5 and the air exhaust edge 4 and are away from the flange plate 2 by a certain distance. In some embodiments, the certain distance may be in the range of 10mm to 50 mm. The certain distance is preferably 20mm. In some embodiments, the width of the score groove 6 can be in the range of 0.12mm to 0.14 mm. Preferably, the width of the engraved groove 6 may be 0.13mm. In some embodiments, the depth of the score groove 6 can be in the range of 0.2mm to 0.9 mm. Preferably, the depth of the engraved groove 6 is 0.5mm. In a preferred embodiment, the comparison sample may be made of an aluminum alloy material. In addition, the control sample may be made of any other material deemed appropriate by one skilled in the art. In a preferred embodiment, the surface of the blade body 3 may be coated with ES205 enamel. In addition, the enamel may be any other coating material deemed appropriate by one skilled in the art. In some embodiments, the thickness of the enamel may be in the range of 0.025mm to 0.038 mm. Preferably, the thickness of the enamel may be 0.029mm. In some embodiments, the surface of the blade body 3 may also be free of enamel paint. By adopting the eddy current flaw detection process, flaw detection can be carried out on the air inlet and outlet edges under the condition of removing the coating, and flaw detection can be carried out under the condition of not removing the coating, so that the flaw detection efficiency is improved, and good economic performance is ensured.

FIG. 2 illustrates a flow chart of a method of inspecting a rotor blade using the above-described comparison sample according to an exemplary embodiment of the present disclosure. The present disclosure provides a method of inspecting a rotor blade using the above-described comparison sample. Preferably, the rotor blade may be a rotor blade of a low-pressure compressor. In particular, the rotor blade may be a 2-4 stage rotor blade of a low-pressure compressor of an aircraft engine. The method may comprise the steps of: s1, initializing an eddy current flaw detector. Preferably, the eddy current flaw detector is of the type SMART5097. Additionally, the eddy current flaw detector may be any other type of eddy current flaw detector deemed appropriate by one skilled in the art. And S2, debugging the eddy current flaw detector by using the comparison sample piece, so that when the eddy current flaw detector is used for detecting flaws of the comparison sample piece, the eddy current flaw detector can give an alarm to indicate that flaws are detected. The comparison sample piece can be used for adjusting the detection sensitivity of the eddy current flaw detector, determining the acceptance level and ensuring the accuracy of the detection result. In addition, the comparison sample is usually engraved with an artificial defect groove which is similar to or slightly smaller than the natural crack of the detected part. The eddy current flaw detector can ensure that artificial defects on the comparison sample piece are detected by using the debugging parameters of the comparison sample piece, thereby ensuring that the defects (namely, natural cracks) are detected when real parts are detected. The comparison sample piece can include: a root 1, the root 1 having a through hole, the through hole being located in the middle of the root 1; a platform 2, the root 1 is located on one side of the platform 2 and abuts against the platform 2; and a blade body 3, said blade body 3 being located on the other side of said rim plate 2 and abutting against said rim plate 2, said blade body 3 comprising: the exhaust edge 4 is positioned at the upper edge of the blade body 3; a gas inlet edge 5, wherein the gas inlet edge 5 is positioned at the lower edge of the blade body 3; and the two ends of the notch 6 are respectively positioned at the positions 20mm away from the edge plate by the air inlet edge 5 and the air exhaust edge 4. The width of the score groove 6 may be 0.13mm and the depth 0.5mm. The reference sample may have the same or similar specification, brand, heat treatment state, surface state, and electromagnetic properties as the rotor blade (i.e., the object to be inspected). Artificial defects of specified size and shape can be machined on the comparison sample. The method may further comprise: and S3, recording detection parameters of the eddy current flaw detector during alarming, namely obtaining the detection parameters of the eddy current flaw detector and storing the detection parameters in the eddy current flaw detector. Preferably, the detection parameters may include one or more of: frequency value, gain, phase, digital filtered value, high pass filtered frequency, and low pass filtered frequency. In some embodiments, the frequency value may be in the range of 470 to 490 kHz. The frequency value may preferably be 476.2kHz. In some embodiments, the gain may be in the range of 30 to 40 dB. The gain may preferably be 35dB. In some embodiments, the phase may be in the range of 200 to 220 DEG. The phase may preferably be 201DEG. Preferably, the digital filter value may be 4.0, the high-pass filter frequency may be 3.0Hz, and the low-pass filter frequency may be 88.0Hz. The detection parameters may further include a pre-gain and a drive value. In some embodiments, the pre-gain is in the range of 20 to 40dB and the drive value is in the range of 3-6. The pre-gain may preferably be 25dB and the drive value may preferably be 5. The method may further comprise: and S4, flaw detection is carried out on the rotor blade by using the eddy current flaw detector based on the recorded detection parameters. Before S4, the rotor blade may also be cleaned to remove dirt, eliminating interference with the detection. The method may further comprise: s5, responding to the alarm of the eddy current flaw detector, and determining that the rotor blade has the defect.

More specific parameters of the eddy current flaw detector obtained in the method according to the exemplary embodiment of the present disclosure are shown in table 1 below.

TABLE 1

The technical scheme of the invention adopts the method and the device, can carry out flaw detection inspection on the premise of not damaging the surface anticorrosive coating of the rotor blade of the low-pressure compressor of the aircraft engine, thereby finding out tiny cracks on the upper surface and the near surface of the air inlet and exhaust edge of the rotor blade, preventing the engine blade from breaking and other faults in the working process, having good economic benefit, good operability, high efficiency and high detection sensitivity. The implementation of the technical scheme marks that a factory has detection capability on cracks and defects of the inlet and exhaust edges of the 2 nd to 4 th-stage rotor blades of the low-pressure compressor of the aero-engine, meanwhile, technical reference is provided for eddy current detection of other spare parts, and the repair reliability and the product quality of the spare parts of the aero-engine are improved.

In the description provided herein, numerous specific details are set forth. However, it is understood that embodiments of the disclosure may be practiced without these specific details. In some embodiments, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description.

While exemplary embodiments of the present invention have been shown and described herein, it will be readily understood by those skilled in the art that such embodiments are provided by way of example only. Numerous modifications, changes, and substitutions will now occur to those skilled in the art without departing from the invention. It should be understood that various alternatives to the embodiments of the invention described herein may be employed in practicing the invention. It is intended that the following claims define the scope of the invention and that methods and structures within the scope of these claims and their equivalents be covered thereby.

Claims

1. A contrasting sample for a rotor blade comprising:

platform, root and blade body, wherein

The platform is placed between the root and the main blade for isolating the root from the main blade, the root being located on one side of the platform and abutting the platform; the root part is provided with a through hole which is positioned in the middle of the root part; the blade body is located on the other side of the platform and abuts against the platform, the blade body comprising:

the exhaust edge is positioned at the upper edge of the blade body;

the air inlet edge is positioned at the lower edge of the blade body; and

and the two ends of the notch are respectively positioned on the air inlet edge and the air exhaust edge and are away from the edge plate by a certain distance.

2. The comparative sample according to claim 1, wherein the certain distance is 20mm.

3. The comparative sample according to claim 1, wherein the width of the engraved groove is 0.13mm.

4. The comparative sample according to claim 1, wherein the depth of the engraved groove is 0.5mm.

5. The comparative sample according to claim 1, wherein the comparative sample is made of an aluminum alloy material.

6. The comparative sample of claim 1, wherein the surface of the body is coated with ES205 enamel.

7. A method of inspecting a rotor blade using the comparative sample of claims 1-6, comprising the steps of:

s1, initializing an eddy current flaw detector;

s2, debugging the eddy current flaw detector by using the comparison sample piece, so that when the eddy current flaw detector is used for detecting flaws on the comparison sample piece, the eddy current flaw detector can give an alarm to indicate that flaws are detected;

s3, recording detection parameters of the eddy current flaw detector during alarming;

s4, flaw detection is carried out on the rotor blade by using the eddy current flaw detector based on the recorded detection parameters; and

s5, responding to the alarm of the eddy current flaw detector, and determining that the rotor blade has the defect.

8. The method of claim 7, wherein the detection parameters include one or more of: frequency value, gain, phase, digital filter value, high pass filter frequency, low pass filter frequency, pre-gain, and drive value.

9. The method of claim 8, wherein the frequency value is 476.2kHz, the gain is 35dB, the phase is 201DEG, the digital filter value is 4.0, the high pass filter frequency is 3.0Hz, the low pass filter frequency is 88.0Hz, the pre-gain is 25dB, and the drive value is 5.

10. The method of claim 7, wherein the eddy current flaw detector is model SMART5097.