CN111882539A - Automatic measurement method for aero-engine blade - Google Patents
Automatic measurement method for aero-engine blade Download PDFInfo
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- CN111882539A CN111882539A CN202010738109.0A CN202010738109A CN111882539A CN 111882539 A CN111882539 A CN 111882539A CN 202010738109 A CN202010738109 A CN 202010738109A CN 111882539 A CN111882539 A CN 111882539A
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- 238000000691 measurement method Methods 0.000 title claims abstract description 6
- 238000005259 measurement Methods 0.000 claims abstract description 26
- 238000001514 detection method Methods 0.000 claims abstract description 12
- 238000000034 method Methods 0.000 claims description 17
- 238000004441 surface measurement Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 3
- 238000001816 cooling Methods 0.000 description 2
- 241000233805 Phoenix Species 0.000 description 1
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- 239000002131 composite material Substances 0.000 description 1
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- G06T7/0004—Industrial image inspection
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- G—PHYSICS
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- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T7/00—Image analysis
- G06T7/60—Analysis of geometric attributes
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- G—PHYSICS
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- G06T2207/00—Indexing scheme for image analysis or image enhancement
- G06T2207/10—Image acquisition modality
- G06T2207/10072—Tomographic images
- G06T2207/10081—Computed x-ray tomography [CT]
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Abstract
The invention relates to an automatic measurement method of an aircraft engine blade, which is characterized in that a three-dimensional area array CT detection system is used for scanning a blade to be measured, correction data is obtained through scattered rays, and the obtained data is analyzed, fitted and the like by combining industrial CT software, so that the effect of automatically measuring the wall thickness of a plurality of positions of a plurality of sections of the blade at one time is effectively realized, the efficiency of measuring the wall thickness of a hollow thin-wall blade is greatly improved, and the measurement result is high in accuracy and good in stability.
Description
Technical Field
The invention relates to the technical field of measurement, in particular to an automatic measurement method for an aircraft engine blade.
Background
The blade is one of core parts of an aeroengine and needs to work at a very high temperature, in order to improve the temperature bearing capacity of the blade, the blade is mostly designed in a thin-wall hollow structure, and an inner cavity is used as an air cooling channel to realize composite air cooling of the blade, so the wall thickness is an important geometric dimension index of the hollow blade and directly influences the safety and the service life of the engine. The existing aeroengine blade wall thickness measuring method mostly adopts an ultrasonic measuring method and a two-dimensional linear array industrial CT measuring method, the efficiency of the ultrasonic measuring method and the two-dimensional linear array industrial CT measuring method is not high, and the measuring time is long.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide an automatic measuring method for an aircraft engine blade, which can automatically measure the wall thickness of multiple positions of multiple cross sections of the blade at one time, greatly improve the efficiency of measuring the wall thickness of a hollow thin-walled blade of the aircraft engine, and ensure the accuracy and stability of the measurement result.
In order to achieve the purpose, the technical scheme of the invention is as follows: an automatic measurement method for an aircraft engine blade is characterized in that: the method comprises the following steps of,
s1, scanning the blades of the aircraft engine by adopting a three-dimensional area array CT detection system, and obtaining final CT volume data through scattered ray correction;
s2, importing vgl-format CT volume data acquired in S1 by using industrial CT software, and analyzing the CT volume data by adopting an automatic mode to acquire the boundary of the blade to finish surface measurement of the blade;
s3, establishing a datum plane on the CT volume data by utilizing industrial CT software, and establishing a reference coordinate system;
s4, extracting surface data of CT volume data by using industrial CT software, generating a surface polygon file in stl format, determining the position of a section of the blade to be measured relative to a reference coordinate system, establishing a wall thickness measurement reference point on a 2D view, and fitting and calculating the distance between the reference points to obtain the wall thickness of a single position of the blade;
s5, sequentially measuring the wall thicknesses of the rest positions to be measured in the 2D view section by using an S4 operation mode, completing the wall thickness measurement of all parts of the single section, and measuring the wall thicknesses of other sections of the blade according to the same method;
s6, exporting a vgt format measurement template file by utilizing industrial CT software;
s7, opening the CT volume data, importing the surface polygon file generated in S4, and completing the matching of the CT volume data and the surface polygon file by utilizing a fitting matching function;
and S8, importing the measurement template file in S6 into CT volume data to complete the multi-section and multi-position wall thickness measurement required by the blade regulation.
Further, the three-dimensional area array CT detection system in S1 is a GE phoenix v | tome | x c CT detection system.
Further, the system parameters corresponding to the system scanning detected in S1 include a voltage of 430kV, a current of 1400uA, a filter selection of 6.0mmCu +1.0mmSn, and a projection number of 1600.
Further, the industrial CT software is VGstudio MAX 2.2.
Compared with the prior art, the invention has the advantages that:
the blade to be measured is scanned by adopting the three-dimensional area array CT detection system, the correction data is obtained through the scattered rays, and the obtained data is analyzed, fitted and the like by combining industrial CT software, so that the effect of automatically measuring the wall thickness of a plurality of positions of a plurality of sections of the blade at one time is effectively realized, the efficiency of measuring the wall thickness of the hollow thin-wall blade is greatly improved, and the measurement result has high accuracy and good stability.
Drawings
FIG. 1 is a 2D view of CT volume data section I;
FIG. 2 is a 2D view of the extracted surface at section I;
FIG. 3 is a matching plot of a 2D view of a CT volume data section I and a 2D view of an extracted surface at section I;
fig. 4 is a surface 3D view of extracted CT volume data.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
As shown in fig. 1 to 4, which are schematic diagrams of blade measurement corresponding to the method of the present application, the method for automatically measuring blades of an aircraft engine comprises,
s1, scanning the blades of the aircraft engine by adopting a three-dimensional area array CT detection system, and obtaining final CT volume data through scattered ray correction; in the application, the three-dimensional area array CT detection system is a GE phonix v | tome | x cCT detection system; meanwhile, the corresponding system parameters during scanning of the system are that the voltage is 430kV, the current is 1400uA, the filter plate is selected to be 6.0mmCu +1.0mmSn, and the projection number is 1600;
s2, importing vgl-format CT volume data acquired in S1 by using industrial CT software, and analyzing the CT volume data by adopting an automatic mode to acquire the boundary of the blade to finish surface measurement of the blade;
s3, establishing a datum plane on the CT volume data by utilizing industrial CT software, and establishing a reference coordinate system;
s4, extracting surface data of CT volume data by using industrial CT software, generating a surface polygon file in stl format, determining the position of a section of the blade to be measured relative to a reference coordinate system, establishing a wall thickness measurement reference point on a 2D view, and fitting and calculating the distance between the reference points to obtain the wall thickness of a single position of the blade;
s5, sequentially measuring the wall thicknesses of the rest positions to be measured in the 2D view section by using an S4 operation mode, completing the wall thickness measurement of all parts of the single section, and measuring the wall thicknesses of other sections of the blade according to the same method;
s6, exporting a vgt format measurement template file by utilizing industrial CT software;
s7, opening the CT volume data, importing the surface polygon file generated in S4, and completing the matching of the CT volume data and the surface polygon file by utilizing a fitting matching function;
and S8, importing the measurement template file in S6 into CT volume data to complete the multi-section and multi-position wall thickness measurement required by the blade regulation.
In the present invention, the industrial CT software is VGstudio MAX 2.2. By adopting the method, the blade to be measured is scanned by utilizing the three-dimensional area array CT detection system, the correction data is obtained through the scattered rays, and the obtained data is analyzed, fitted and the like by combining with industrial CT software, so that the effect of automatically measuring the wall thickness of a plurality of positions of a plurality of sections of the blade at one time is effectively realized, the efficiency of measuring the wall thickness of the hollow thin-wall blade is greatly improved, and the measurement result has high accuracy and good stability.
To verify this conclusion, details are given below, and table 1 is a comparison of data 1 measured according to volume data and data 2 measured by using a measurement template after re-importing the volume data after extracting the measurement data on the volume data. According to the comparison, the measurement result obtained by re-importing the volume data after the measurement data on the volume data are extracted and measuring by using the measurement template has higher accuracy.
TABLE 1
While embodiments of the invention have been shown and described, it will be understood by those skilled in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (4)
1. An automatic measurement method for an aircraft engine blade is characterized in that: the method comprises the following steps of,
s1, scanning the blades of the aircraft engine by adopting a three-dimensional area array CT detection system, and obtaining final CT volume data through scattered ray correction;
s2, importing vgl-format CT volume data acquired in S1 by using industrial CT software, and analyzing the CT volume data by adopting an automatic mode to acquire the boundary of the blade to finish surface measurement of the blade;
s3, establishing a datum plane on the CT volume data by utilizing industrial CT software, and establishing a reference coordinate system;
s4, extracting surface data of CT volume data by using industrial CT software, generating a surface polygon file in stl format, determining the position of a section of the blade to be measured relative to a reference coordinate system, establishing a wall thickness measurement reference point on a 2D view, and fitting and calculating the distance between the reference points to obtain the wall thickness of a single position of the blade;
s5, sequentially measuring the wall thicknesses of the rest positions to be measured in the 2D view section by using an S4 operation mode, completing the wall thickness measurement of all parts of the single section, and measuring the wall thicknesses of other sections of the blade according to the same method;
s6, exporting a vgt format measurement template file by utilizing industrial CT software;
s7, opening the CT volume data, importing the surface polygon file generated in S4, and completing the matching of the CT volume data and the surface polygon file by utilizing a fitting matching function;
and S8, importing the measurement template file in S6 into CT volume data to complete the multi-section and multi-position wall thickness measurement required by the blade regulation.
2. The method of claim 1, further comprising:
the three-dimensional area array CT detection system in the S1 is a GE phonix v | tome | x c CT detection system.
3. The method of claim 1, further comprising:
in S1, the system parameters corresponding to the system scan include a voltage of 430kV, a current of 1400uA, a filter selection of 6.0mmCu +1.0mmSn, and a projection number of 1600.
4. The method of claim 1, further comprising:
the industrial CT software is VGstudio MAX 2.2.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010738109.0A CN111882539A (en) | 2020-07-28 | 2020-07-28 | Automatic measurement method for aero-engine blade |
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| CN202010738109.0A CN111882539A (en) | 2020-07-28 | 2020-07-28 | Automatic measurement method for aero-engine blade |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112605541A (en) * | 2020-11-11 | 2021-04-06 | 中国兵器科学研究院宁波分院 | Method for measuring wall damage depth of fuel nozzle laser drilling of aircraft engine |
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| US20120207370A1 (en) * | 2010-12-20 | 2012-08-16 | Benjamin Pooya Fahimian | Systems and Methods for Simultaneous Acquisition of Scatter and Image Projection Data in Computed Tomography |
| CN108549773A (en) * | 2018-04-16 | 2018-09-18 | 西北工业大学 | Mesh parameterization method and the multidisciplinary reliability design optimization method of turbo blade based on the mesh parameterization method |
| CN111259557A (en) * | 2020-01-21 | 2020-06-09 | 山西大学 | Hollow turbine blade wall thickness deviation reverse regulation and control method based on ceramic core positioning compensation |
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2020
- 2020-07-28 CN CN202010738109.0A patent/CN111882539A/en active Pending
Patent Citations (5)
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| US6041132A (en) * | 1997-07-29 | 2000-03-21 | General Electric Company | Computed tomography inspection of composite ply structure |
| US20090066939A1 (en) * | 2007-09-07 | 2009-03-12 | General Electric Company | Method for automatic identification of defects in turbine engine blades |
| US20120207370A1 (en) * | 2010-12-20 | 2012-08-16 | Benjamin Pooya Fahimian | Systems and Methods for Simultaneous Acquisition of Scatter and Image Projection Data in Computed Tomography |
| CN108549773A (en) * | 2018-04-16 | 2018-09-18 | 西北工业大学 | Mesh parameterization method and the multidisciplinary reliability design optimization method of turbo blade based on the mesh parameterization method |
| CN111259557A (en) * | 2020-01-21 | 2020-06-09 | 山西大学 | Hollow turbine blade wall thickness deviation reverse regulation and control method based on ceramic core positioning compensation |
Non-Patent Citations (3)
| Title |
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| VOLUME GRAPHICS GMBH: "《MAX 2.2 Reference Manual》", 31 May 2012 * |
| 周莹: "航空发动机涡轮叶片数字射线成像研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112605541A (en) * | 2020-11-11 | 2021-04-06 | 中国兵器科学研究院宁波分院 | Method for measuring wall damage depth of fuel nozzle laser drilling of aircraft engine |
| CN112605541B (en) * | 2020-11-11 | 2022-09-06 | 中国兵器科学研究院宁波分院 | Method for measuring wall damage depth caused by laser drilling of fuel nozzle of aircraft engine |
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Application publication date: 20201103 |