CN108917687B - Method for detecting tiny cambered surfaces of front edge and rear edge of blade of aero-engine - Google Patents
Method for detecting tiny cambered surfaces of front edge and rear edge of blade of aero-engine Download PDFInfo
- Publication number
- CN108917687B CN108917687B CN201810383709.2A CN201810383709A CN108917687B CN 108917687 B CN108917687 B CN 108917687B CN 201810383709 A CN201810383709 A CN 201810383709A CN 108917687 B CN108917687 B CN 108917687B
- Authority
- CN
- China
- Prior art keywords
- blade
- region
- nurbs
- rear edge
- arc
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/20—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring contours or curvatures, e.g. determining profile
Abstract
The invention belongs to the field of micro arc surface characteristic detection, and provides a method for detecting a micro arc surface of the front edge and the rear edge of an aircraft engine blade, which comprises the following steps: 1. measuring the blade under different poses through detection equipment to respectively acquire surface measurement data of each region and a junction region of each region; 2. respectively carrying out surface fitting on each region and the boundary region of each region by a NURBS surface fitting method to obtain a plurality of NURBS surfaces; 3. splicing a plurality of NURBS curved surfaces by adopting a curved surface splicing method to obtain an NURBS integral curved surface model representing the whole surface appearance of the blade; 4. carrying out measuring head radius compensation on the NURBS integral curved surface model to obtain a corrected blade curved surface model; 5. and extracting the section characteristic lines of the blade from the corrected blade curved surface model, and extracting the front and rear edge characteristic data of the blade from the section characteristic lines to obtain the front and rear edge micro arc surface characteristic parameters of the blade. The invention improves the detection precision and repeatability.
Description
Technical Field
The invention belongs to the technical field of micro-arc surface characteristic detection, and particularly relates to a method for detecting a micro-arc surface of the front edge and the rear edge of an aircraft engine blade.
Background
The mechanical manufacturing is the supporting industry of national economy, national defense and scientific research, and determines a national economic pattern and competitiveness. One important trend in the machine manufacturing industry is the complexity and miniaturization of product shapes. The micro arc surface characteristic has been widely applied to transmission devices of various high-speed and heavy-load large-scale mechanical equipment due to a plurality of unique advantages of the micro arc surface characteristic applied to key parts of complex parts. The measurement and detection of the geometric quantity of the key parts of the complex parts are the basis and the prerequisite for the development of the machine manufacturing industry, and the improvement of the machining precision is always closely related to the development level of the geometric quantity measurement and detection technology.
At present, in the field of micro arc surface characteristic detection research, detection of a micro arc (an arc corresponding to a central angle below 30 degrees) is basically taken as a research object, but for the micro arc surface of the front edge and the rear edge of an aircraft engine blade, the measurement precision of detection equipment is high, and the measurement repeatability of an arc surface characteristic parameter detection result is poor. The measurement of the tiny arc is always a difficult problem in the field of precision measurement, and the shorter the arc length of the arc is, the worse the measurement repeatability is; the smaller the radius of the arc, the lower the detection accuracy. The problem of measuring the tiny arc is that no matter what measuring instrument is used, a point must be taken on the measured tiny arc, and due to the influence of various factors, a point taking error is inevitably generated, and the error is amplified to a great extent.
In view of the defects of the detection method, the invention provides the high-precision detection method for the micro arc surface, which can be used for overall measurement and local evaluation, so that the defects of the existing detection method are overcome, and the detection precision of the micro arc surface is effectively improved with lower mathematical calculation difficulty, which is particularly important.
Disclosure of Invention
The invention overcomes the defects of the prior art, and solves the technical problems that: the method for detecting the micro arc surfaces of the front edge and the rear edge of the blade of the aircraft engine is provided, so that the detection accuracy of the micro arc surfaces of the front edge and the rear edge is improved.
In order to solve the technical problems, the invention adopts the technical scheme that: a method for detecting a tiny arc surface of the front edge and the rear edge of an aircraft engine blade comprises the following steps:
step 1: partitioning the surface of the blade, and then measuring the blade through detection equipment at different poses so as to respectively obtain surface measurement data of each region and a junction region of each region;
step 2: respectively carrying out surface fitting on the surface measurement data of each region and the junction region of each region by a NURBS surface fitting method to obtain a plurality of NURBS surfaces;
and step 3: splicing the plurality of NURBS curved surfaces obtained by the fitting in the step (2) by adopting a curved surface splicing method to obtain a NURBS integral curved surface model representing the whole surface appearance of the blade;
and 4, step 4: measuring head radius compensation is carried out on the NURBS integral curved surface model obtained in the step 3, and a modified blade curved surface model is obtained;
and 5: and extracting the section characteristic lines of the blade from the corrected blade curved surface model, and extracting the front and rear edge characteristic data of the blade from the section characteristic lines to obtain the front and rear edge micro arc surface characteristic parameters of the blade.
In the step 1, the surface of the blade is partitioned into a basin region, a back region and an arc surface region, and then the blade is measured in different poses through detection equipment, so as to respectively obtain surface measurement data of the basin region, the back region, an upper arc surface region, a lower arc surface region and junction regions of the arc surface, the basin region and the back region.
In the step 2, surface fitting is respectively performed on the obtained surface measurement data of the leaf basin region, the leaf back region, the upper arc surface region, the lower arc surface region and the junction region of the arc surface and the leaf basin and the leaf back by a NURBS surface fitting method, so that a plurality of NURBS surfaces are obtained.
Compared with the prior art, the invention has the following beneficial effects:
1. the method for detecting the micro arc surface of the front edge and the rear edge of the blade of the aero-engine is based on a micro arc overall measurement local evaluation method, adopts a method of firstly performing overall fitting and then performing local separation evaluation, avoids errors caused by the fact that a point needs to be taken on a measured arc by a traditional method, breaks through the limitation of the traditional measurement method, improves the measurement precision of a measurement result, greatly reduces the detection cost, and greatly improves the repeatability of the measurement result;
2. the method for detecting the micro arc surface can be applied to the detection of the blade of the aero-engine and the detection field of the micro arc surface characteristics of various high-speed and heavy-load large-scale mechanical equipment transmission devices including a high-power industrial gas turbine and a railway locomotive driving system.
Drawings
FIG. 1 is a schematic diagram of measurement data acquisition according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of NURBS surface fitting in an embodiment of the present invention;
FIG. 3 is a schematic diagram of a NURBS global curved surface model representing the entire surface topography of a blade obtained by stitching a plurality of NURBS curved surfaces according to an embodiment of the present invention;
FIG. 4 is a schematic diagram illustrating a measurement head radius compensation performed on a modified blade curved surface model according to an embodiment of the present invention;
FIG. 5 is a schematic diagram illustrating the extraction of the data of the characteristic line of the micro arc surface according to the embodiment of the present invention;
FIG. 6 is a schematic diagram illustrating evaluation of characteristic parameters of a micro arc surface in an embodiment of the present invention;
FIG. 7 is a schematic illustration of a prior art measurement;
fig. 8 is another schematic of a prior art measurement.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below, and it is obvious that the described embodiments are some embodiments of the present invention, but not all embodiments; all other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The basic idea of the invention is as follows: aiming at the micro arc surface characteristics of the blades of the aero-engine with the size of millimeter level or even submillimeter level, a novel detection method for integrally measuring the characteristic parameters of the micro arc surface of local evaluation is provided from the overall aspect based on the model design of tangency and continuity of adjacent characteristic curved surfaces of the surfaces of parts and parts according to the overall appearance characteristics of the parts.
As shown in fig. 1 to 6, a method for detecting a micro arc surface of a front edge and a rear edge of an aircraft engine blade provided by an embodiment of the invention includes the following steps:
step 1: and acquiring measurement data. The acquisition of measurement data is a prerequisite for model evaluation. For a blade-type workpiece with complex characteristics, all measurement data of the surface of the blade cannot be acquired under the same pose of the detection equipment. Therefore, all the measurement data of the blade surface need to be acquired in different regions under different poses of the detection equipment. As shown in FIG. 1, the surface of the blade is partitioned, and each area of the surface of the blade is rapidly scanned by using a contact type measuring head, so that the measurement data of the surface of the blade is acquired; when the surface of the blade is partitioned, the blade can be divided into a blade basin region, a blade back region and an arc surface region, and then the blade is measured under different poses through detection equipment, so that surface measurement data of the blade basin region, the blade back region, an upper arc surface region, a lower arc surface region and junction regions of the arc surface region, the blade basin region and the blade back region are respectively obtained.
Step 2: as shown in fig. 2, by the NURBS surface fitting method, surface fitting is performed on the irregular measurement data on the surface of each individual region, that is, surface fitting is performed on the measurement data obtained from the surface of the basin region, the back region, the upper arc region, the lower arc region, and the junction region between the arc surface and the basin and the back of the leaf, so as to obtain a plurality of NURBS surfaces.
And step 3: and (3) performing surface splicing on the plurality of NURBS curved surfaces obtained by the step (2) by adopting a surface splicing method to obtain a NURBS integral surface model. The curved surface splicing is that a curved surface (called as a father surface) is extended to another curved surface (called as a mother surface) according to a certain direction, and the connection part of the extended curved surface and the father surface and the mother surface meets a certain smooth condition. Splicing the plurality of NURBS curved surfaces obtained by the fitting in the step (2) by the curved surface splicing method to restore the overall original appearance of the measured blade part, thereby obtaining an NURBS overall curved surface model representing the overall surface appearance of the blade;
and 4, step 4: as shown in fig. 4, performing measurement head radius compensation on the NURBS overall curved surface model obtained in step 3 to obtain a modified blade curved surface model; because the measured data contains errors caused by the size of the measuring head, an actual surface mathematical model of the measured object can be obtained through measuring head radius compensation.
And 5: as shown in fig. 5, a section characteristic line of the blade is extracted from the corrected blade curved surface model, then characteristic data of the micro arc surfaces at the front and rear edges of the blade are extracted from the section characteristic line, and finally the extracted micro arc surface data is subjected to data partition processing to obtain the characteristic parameters of the micro arc surfaces at the front and rear edges of the blade. As shown in fig. 6, the schematic diagram is a schematic diagram of final evaluation of the blade micro arc characteristic parameters after extracting the blade micro arc characteristic.
As shown in fig. 7 and 8, for the schematic diagram of the measurement in the prior art, the small circle located inside the semi-circle abc and the small circle located outside the semi-circle abc in fig. 7 and 8 represent the measurement error, and since the position of the measurement error is random with respect to the circular arc, and may appear outside the circular arc, and may also appear inside the circular arc, when the measurement error is located inside the semi-circle, the value of the actually measured circular arc radius r1 may be smaller, and when the measurement error is located outside the semi-circle, the value of the actually measured circular arc radius r2 may be larger, so the measurement error in the prior art may be larger, and the measurement repeatability is poor. The invention uses the integral measurement method, because not only the measured arc is measured, but also other parts on the whole are measured, the measurement error is not only the small arc pointed by the arrow of the figure, and the positions of the rest measurement errors are random and can appear on the inner side and the outer side, so the total errors can be averaged when the integral measurement method is used for measurement, and the measurement effect is better than that of the traditional measurement method.
According to the technical scheme, when the micro cambered surface of the aero-engine blade disc is detected, the traditional measurement method for modeling calculation only aiming at the micro cambered surface of the blade to be detected is abandoned, the modeling analysis is only carried out on the micro cambered surface of the blade to be detected from the whole situation according to the characteristics of the micro cambered surface with the size of millimeter level or even submillimeter level, the extending connection part of the micro cambered surface of the blade of the aero-engine to be detected is taken into consideration together according to the overall appearance characteristics of the blade of the aero-engine, and the integral measurement is carried out on the micro cambered surface of the blade based on the model design principle that the adjacent characteristic curved surfaces on the surface of the blade of the aero-engine are. Therefore, the novel method for detecting the characteristic parameters of the tiny cambered surface of the blade of the aero-engine based on the integral measurement and local evaluation is provided, the high precision is ensured, and the measurement repeatability of the detection result is obviously improved.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (3)
1. A method for detecting micro arc surfaces of the front edge and the rear edge of an aircraft engine blade is characterized by comprising the following steps:
step 1: partitioning the surface of the blade, and then measuring the blade through detection equipment at different poses so as to respectively obtain surface measurement data of each region and a junction region of each region;
step 2: respectively carrying out surface fitting on the surface measurement data of each region and the junction region of each region by a NURBS surface fitting method to obtain a plurality of NURBS surfaces;
and step 3: splicing the plurality of NURBS curved surfaces obtained by the fitting in the step (2) by adopting a curved surface splicing method to obtain a NURBS integral curved surface model representing the whole surface appearance of the blade;
and 4, step 4: measuring head radius compensation is carried out on the NURBS integral curved surface model obtained in the step 3, and a modified blade curved surface model is obtained;
and 5: and extracting the section characteristic lines of the blade from the corrected blade curved surface model, and extracting the front and rear edge characteristic data of the blade from the section characteristic lines to obtain the front and rear edge micro arc surface characteristic parameters of the blade.
2. The method for detecting the micro arc surface of the front edge and the rear edge of the aircraft engine blade as claimed in claim 1, wherein in the step 1, the surface of the blade is partitioned into a blade basin area, a blade back area and an arc surface area, and then the blade is measured by detection equipment at different poses so as to respectively obtain surface measurement data of the blade basin area, the blade back area, an upper arc surface area, a lower arc surface area and a junction area of the arc surface and the blade basin and the blade back.
3. The method for detecting the micro arc surfaces of the front edge and the rear edge of the aircraft engine blade according to claim 2, wherein in the step 2, the obtained surface measurement data of the basin region, the back region, the upper arc surface region, the lower arc surface region and the junction region of the arc surfaces and the basin and the back of the blade are subjected to surface fitting through a NURBS surface fitting method to obtain a plurality of NURBS surfaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810383709.2A CN108917687B (en) | 2018-04-26 | 2018-04-26 | Method for detecting tiny cambered surfaces of front edge and rear edge of blade of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810383709.2A CN108917687B (en) | 2018-04-26 | 2018-04-26 | Method for detecting tiny cambered surfaces of front edge and rear edge of blade of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108917687A CN108917687A (en) | 2018-11-30 |
| CN108917687B true CN108917687B (en) | 2020-08-04 |
Family
ID=64403236
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810383709.2A Active CN108917687B (en) | 2018-04-26 | 2018-04-26 | Method for detecting tiny cambered surfaces of front edge and rear edge of blade of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108917687B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111806720B (en) * | 2020-06-24 | 2021-12-07 | 成都飞机工业（集团）有限责任公司 | Rectification skin construction method based on measured data of wing body butt joint |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103777570A (en) * | 2014-01-07 | 2014-05-07 | 浙江大学 | Machining error rapid detection and compensation method based on NURBS curved surface |
| CN106202822A (en) * | 2016-07-27 | 2016-12-07 | 西北工业大学 | B-spline surface model reconstruction method towards blade adaptive machining |
| CN106767524A (en) * | 2016-11-22 | 2017-05-31 | 江苏大学 | A kind of hydraulic spoon of blade detection method and device |
| CN107067472A (en) * | 2016-09-29 | 2017-08-18 | 北京理工大学 | A kind of geometric error characterizing method reconstructed based on nurbs surface |
| CN107357959A (en) * | 2017-06-14 | 2017-11-17 | 西安交通大学 | A kind of high-precision blade profile characteristic parameter extraction method |
| CN107451378A (en) * | 2017-09-05 | 2017-12-08 | 电子科技大学 | A kind of three-dimensional coordinates measurement blade profile samples point extracting method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8310481B2 (en) * | 2007-10-12 | 2012-11-13 | Edward Ernest Bailey | Computer aided design method for enhancement of local refinement through T-splines |
| CN104330065B (en) * | 2014-07-28 | 2017-03-29 | 河南科技大学 | A kind of spiral bevel gear flank of tooth curvature interference method of inspection |
| CN105737762B (en) * | 2016-05-09 | 2018-03-16 | 中国民用航空飞行学院 | A kind of blade of aviation engine profile measurement method |
| CN106354927B (en) * | 2016-08-29 | 2019-05-10 | 西北工业大学 | A kind of construction method of precision forged blade front and rear edge adaptive machining Optimized model |
-
2018
- 2018-04-26 CN CN201810383709.2A patent/CN108917687B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103777570A (en) * | 2014-01-07 | 2014-05-07 | 浙江大学 | Machining error rapid detection and compensation method based on NURBS curved surface |
| CN106202822A (en) * | 2016-07-27 | 2016-12-07 | 西北工业大学 | B-spline surface model reconstruction method towards blade adaptive machining |
| CN107067472A (en) * | 2016-09-29 | 2017-08-18 | 北京理工大学 | A kind of geometric error characterizing method reconstructed based on nurbs surface |
| CN106767524A (en) * | 2016-11-22 | 2017-05-31 | 江苏大学 | A kind of hydraulic spoon of blade detection method and device |
| CN107357959A (en) * | 2017-06-14 | 2017-11-17 | 西安交通大学 | A kind of high-precision blade profile characteristic parameter extraction method |
| CN107451378A (en) * | 2017-09-05 | 2017-12-08 | 电子科技大学 | A kind of three-dimensional coordinates measurement blade profile samples point extracting method |
Non-Patent Citations (3)
| Title |
|---|
| 一种基于激光传感器快速检测透平叶片的方法;李兵等;《光子学报》;20171130;第46卷(第11期);第1128002-2—1128002-11页 * |
| 航空发动机叶片截面特征参数提取技术研究;马雯琦;《中国优秀硕士学位论文全文数据库 信息科技辑》;20150515(第5期);正文第1.4节、第二章，图2-1—2-11 * |
| 逆向工程曲面重建及实验应用研究;张德海等;《锻压技术》;20160630;第41卷(第6期);第115-121页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108917687A (en) | 2018-11-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110349252B (en) | Method for constructing actual machining curve of small-curvature part based on point cloud boundary | |
| CN106969703B (en) | Method and system for automated formed cooling hole measurement | |
| CN108986048B (en) | Three-dimensional point cloud rapid composite filtering processing method based on line laser scanning | |
| CN107341802B (en) | Corner sub-pixel positioning method based on curvature and gray scale compounding | |
| CN109855562B (en) | Method and device for measuring rail abrasion | |
| CN104392476A (en) | Method of extracting three-dimensional axis of tunnel based on minimum bounding box algorithm | |
| CN104406502B (en) | A kind of gas turbine blades forging stock physical dimension control method and detection model | |
| CN107357959B (en) | High-precision blade section characteristic parameter extraction method | |
| CN109685778B (en) | CT slice-based detection method for several common geometric quantities of mechanical parts | |
| CN102589435A (en) | Efficient and accurate detection method of laser beam center under noise environment | |
| CN114354639B (en) | Weld defect real-time detection method and system based on 3D point cloud | |
| CN113865508B (en) | Automatic detection device and method for through hole rate of sound lining of honeycomb sandwich composite material | |
| CN105627923A (en) | Scan path programming method obtained by leaf dense point cloud on basis of laser ranging | |
| CN111047588A (en) | Imaging measurement method for size of shaft type small part | |
| CN108917687B (en) | Method for detecting tiny cambered surfaces of front edge and rear edge of blade of aero-engine | |
| CN108073747A (en) | Aircraft structure Three Dimensional Design Model quality detecting system and method | |
| CN105184792B (en) | A kind of saw blade wear extent On-line Measuring Method | |
| CN114608461B (en) | Laser scanning measurement method for non-uniform wall thickness parts | |
| CN115482211A (en) | Tunnel overbreak and underexcavation detection method and device, electronic equipment and storage medium | |
| CN105115441A (en) | Feature point extraction automatic segmenting method for profile of revolution solid part | |
| CN104748684B (en) | Visual detection method and device for crankshaft shoulder back chipping | |
| CN105046020A (en) | Automatic identification and correction method used for broken surface defect of airplane complex structural component | |
| CN104199742A (en) | Method for accurately dividing blade cross section character point cloud | |
| CN110021027B (en) | Edge cutting point calculation method based on binocular vision | |
| Mao et al. | A Hybrid Algorithm for the Laser Stripe Centreline Extraction |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |