CN102230786A - Optical-measurement-based method for testing wall thickness of wax pattern for hollow turbine blade - Google Patents
Optical-measurement-based method for testing wall thickness of wax pattern for hollow turbine blade Download PDFInfo
- Publication number
- CN102230786A CN102230786A CN2011100801932A CN201110080193A CN102230786A CN 102230786 A CN102230786 A CN 102230786A CN 2011100801932 A CN2011100801932 A CN 2011100801932A CN 201110080193 A CN201110080193 A CN 201110080193A CN 102230786 A CN102230786 A CN 102230786A
- Authority
- CN
- China
- Prior art keywords
- wax
- pattern
- wall thickness
- tao xin
- wax pattern
- 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.)
- Pending
Links
Images
Abstract
The invention discloses an optical-measurement-based method for testing the wall thickness of a wax pattern for a hollow turbine blade, which comprises the following steps of: using an optical scanner to obtain ceramic core data and wax pattern data; pre-registering and fine-registering the ceramic core and the wax pattern in sequence; controlling the measurement models of the ceramic core and the wax pattern to intersect with planes which are vertical to the measurement models so as to obtain the intersecting lines serving as the corresponding section lines of the ceramic core and wax pattern located in the layers of the vertical plane, and obtaining at least five such section lines; calculating the wall thickness of the wax pattern in each layer by using a shortest distance method according to the section lines of the ceramic core and wax pattern in each layer; and carrying out superposition on the wall thickness distribution of each layer along the layer heights so as to obtain the 3D wall thickness distribution of the wax pattern. The invention has low cost and is easy and convenient to operate. In addition, the invention can ensure the correctness and stability of the wall thickness calculation, thereby easily realizing in-batch measurements.
Description
Technical field
The present invention relates to a kind of detection method of hollow turbine vane wax-pattern wall thickness, be applicable to the detection of hot investment casting wax-patterns such as Aeronautics and Astronautics, weapons.
Background technology
The casting method commonly used of blade is precision-investment casting, be subjected to influence of various factors such as casting technique, smart foundry work dress, material, the smart casting technology of China turbo blade with big gap is abroad arranged, the smart casting blade precision of domestic development is on the low side, quality is unstable, rejection rate is very high, is the bottleneck of the novel aeromotor development of restriction China always.The wall thickness of turbo blade mainly guarantees by the wall thickness of essence casting wax pattern, by detecting and reject the essence casting wax pattern that produces wall thickness segregation drift, can effectively improve smart casting rate.
At present, being applied to the wax-pattern detection technique mainly contains following several:
Supercritical ultrasonics technology, measuring accuracy are not high, and have the measurement blind area, and its measurement lower limit is restricted, and can only obtain the wall thickness at some specified point place, can not do comprehensive wall thickness detecting.
Electric vortex method is subjected to the influence of probe diameter and test specimen physical dimension, and measuring error is big.
Thermoprobe method, point of every measurement will stay next pin hole, must fill up immediately after the measurement, and is so both time-consuming, influences the blade surface quality again.And because blade profile has torsion resistance, cause the normal direction that is difficult for grasping measuring point when measuring, this will cause than mistake.
CT image wall thickness detecting method, measuring accuracy is higher, but Measuring Time is long, cost is high.
The measurement that more than existing detection method has is not accurate enough, and the measurement that has can destroy wax-pattern itself, and the measurement cost that has is too high, therefore all can not be as the means that detect in batch.
Summary of the invention
Can not take into account complete detection and problem cheaply based on existing detection method, the invention provides a kind of hollow turbine vane wax-pattern wall thickness detecting method based on optical measurement.Its light harvesting is learned measurement, UG secondary development in one, has realized the low cost of hollow turbine vane wax-pattern, accurate, comprehensive three-dimensional the detection.
The technical solution adopted for the present invention to solve the technical problems comprises the steps:
Obtain the Tao Xin data with optical scanner, again Tao Xin is pressed wax, measure the wax-pattern data with optical scanner;
Tao Xin and wax-pattern by optical scanning are twice measurement result, so location difference.At first, choosing on Tao Xin and wax-pattern at corresponding 3, to carry out pre-registration (be that Tao Xin roughly aligns with wax-pattern, make the positioning table and the exhaust limit part of Tao Xin and wax-pattern fit substantially), choose the feature common sides of Tao Xin and wax-pattern again and carry out meticulous registration (being that Tao Xin accurately aligns with cured mould);
With the measurement model of Tao Xin and wax-pattern with their perpendicular Plane intersects, the intersection that obtains is with the Tao Xin on perpendicular place, the plane aspect of Tao Xin and wax-pattern model and the corresponding section line of wax-pattern.The quantity of section line and position can obtain arbitrarily according to demand, for the three-dimensional wall thickness that is combined into is tried one's best comprehensively accurately, generally get 5 section lines at least, such as the corresponding section line of intercepting on the wall thickness height and position that detects at needs, also can obtain the whole wall thickness data of blade according to highly even sectioned line on blade;
According to the section line of Tao Xin and each layer of wax-pattern position, utilization bee-line method calculates the wall thickness of wax-pattern in each layer position.So-called bee-line method is meant the respective point that calculates on the Tao Xin section line bee-line to same level wax-pattern section line, with this apart from as the wall thickness of wax-pattern herein;
With the direction stack of the Thickness Distribution of each aspect wax-pattern, can obtain the three-dimensional Thickness Distribution of wax-pattern along the aspect height.
The invention has the beneficial effects as follows: the utilization optical measurement, the measurement cost of individual blade wax-pattern is low, is applicable to measure in batch to detect; Data processing utilization UG secondary development program is carried out automatically, has friendly operating user interface simply, conveniently; Bee-line method calculated wall thickness guarantees accuracy and stability that wall thickness calculates; Thereby the measurement that has realized hollow turbine vane wax-pattern wall thickness is calculated, and cost is low, measures comprehensively accurately, is easy to realize the batch detection measurement.
The present invention is further described below in conjunction with drawings and Examples.
Description of drawings
Fig. 1 is a hollow turbine vane wax-pattern wall thickness calculation flow chart.
Fig. 2 is the selection figure of three reference point of pre-registration.
Fig. 3 is that the characteristic face of meticulous registration is chosen figure.
Fig. 4 is subregion explanation of the complicated Tao Xin wax-pattern of certain model cross section and wall thickness profile figure.
Fig. 5 is the complicated Tao Xin wax-pattern of certain a model Thickness Distribution curve map.
Embodiment
Hollow turbine vane wax-pattern wall thickness computation process of the present invention is as Fig. 1.With certain model turbo blade Tao Xin and wax-pattern is example:
Step 1:
Obtain the outline point cloud model of blade Tao Xin and corresponding wax-pattern respectively by the ATOS optical scanner.
Step 2:
Shape data to blade Tao Xin and wax-pattern carries out three-dimensional registration.Because accurate registration Algorithm of the present invention is the closest approach process of iteration (SVD-ICP) based on singular value, requires position and orientation between the model subject to registration very approaching, could guarantee the convergence of registration Algorithm.For this reason, use the model method for registering realization blade wax-pattern measurement data at three reference mark and the pre-registration of blade Tao Xin measurement data, make position of the two and orientation enough approaching.As Fig. 2, on blade wax-pattern measurement model, select three impact points, on blade Tao Xin measurement model, choose three orientation corresponding reference points 1,2,3.By three impact points being transformed to the position of three reference point, find the solution the pre-registration transformation matrix that blade is measured cloud data and blade cad model.
Because Tao Xin and wax-pattern are the different measuring body surface, therefore can not adopt traditional measurement model and design a model between the whole registration method.Therefore the present invention adopts the method for registering based on characteristic face, common sides with Tao Xin and wax-pattern measurement model is a characteristic face, shown among Fig. 34,5,6, carry out closest approach iteration (SVD-ICP) registration based on singular value, the feature common sides can be carried out the control of 6 degree of freedom directions.4 are exhaust sapwood charge level among Fig. 3, in order to control the positive and negative property of two registration model y, z direction; 5 is the positioning table side, in order to the degree of freedom of three rotary freedoms controlling two registration models and y, z direction; 6 is the positioning table end face, in order to control the degree of freedom of two registration model x directions.Thus, two models accurately can be joined under the situation of not dwindling its distortion.
Step 3:
Obtain the two-dimensional section line behind the registration again.After accurately registration is finished, the intersection that utilization plane and surface intersection draw, be the principle of the section line of curved surface on this plane, with the measurement model of Tao Xin and wax-pattern with their perpendicular Plane intersects, the intersection that obtains is with the Tao Xin on perpendicular place, the plane aspect of Tao Xin and wax-pattern model and the corresponding section line of wax-pattern.
Step 4:
Then calculate wax-pattern wall thickness algorithm computation and go out wall thickness according to the bee-line method.Obtain Tao Xin and wax-pattern behind the section line on the same aspect as Fig. 4 (a), wherein, L1-L5 is respectively five longitudinal ribs of Tao Xin at leaf back five positions from the trailing edge to the leading edge successively, and L1 '-L5 ' is respectively five longitudinal ribs of Tao Xin at leaf pelvic surface of sacrum five positions from the trailing edge to the leading edge successively.Utilization bee-line method is calculated wax-pattern each position wall thickness in this aspect.During factory's actual blade wax-pattern thickness detects at present, use supersonic thickness meter to measure along the distance of the normal direction arrival inside surface at blade wax-pattern outer surface measuring point place.Because the modus operand line method may appear at certain some place and takes place than uncertain program miscounts such as large deviations because of the trickle turnover of section line causes normal direction during optical measurement was calculated, thereby cause calculating inaccurate, the wall thickness phenomenon takes place to amplify.So carrying out automatically for blade wax-pattern wall thickness detecting, according to the wall thickness detecting technology that is fit to optical measurement data, the present invention provides the stronger wax-pattern wall thickness definition of a kind of constraint, the bee-line that a bit arrives same aspect wax-pattern section line on the definition Tao Xin section line is the wall thickness at this some place, the UF_MODL_ask_minimum_dist of this paper bee-line utilization UG secondary development the inside finishes, by the institute on the Tao Xin section line is carried out the closest approach iteration a little, can obtain the wall thickness at any point place on this aspect section line, the result is shown in Fig. 4 (b).
Step 5:
So, then the wall thickness gauge of the some aspects of hollow turbine vane wax-pattern calculates, and the wall thickness with each aspect carries out three-dimensional stack demonstration again, and then the three-dimensional wall thickness of whole blade is obtained.Three-dimensional wall thickness result as shown in Figure 5.
Claims (2)
1. one kind based on optical measurement hollow turbine vane wax-pattern wall thickness detecting method, it is characterized in that comprising the steps:
Step 1
Obtain the Tao Xin data with optical scanner, again Tao Xin is pressed wax, measure the wax-pattern data with optical scanner;
Step 2
Choose correspondence on Tao Xin and wax-pattern 3 are carried out pre-registration, choose the feature common sides of Tao Xin and wax-pattern again and carry out meticulous registration;
Step 3
With the measurement model of Tao Xin and wax-pattern with their perpendicular Plane intersects, the intersection that obtains is with the Tao Xin on perpendicular place, the plane aspect of Tao Xin and wax-pattern model and the corresponding section line of wax-pattern; At least get 5 section lines;
Step 4
According to the section line of Tao Xin and each layer of wax-pattern position, utilization bee-line method calculates the wall thickness of wax-pattern in each layer position;
Step 5
With the direction stack of the Thickness Distribution of each aspect wax-pattern, can obtain the three-dimensional Thickness Distribution of wax-pattern along the aspect height.
2. according to claim 1 based on optical measurement hollow turbine vane wax-pattern wall thickness detecting method, it is characterized in that: described bee-line method is meant the respective point that calculates on the Tao Xin section line bee-line to same level wax-pattern section line, with this apart from as the wall thickness of wax-pattern herein.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100801932A CN102230786A (en) | 2011-03-31 | 2011-03-31 | Optical-measurement-based method for testing wall thickness of wax pattern for hollow turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100801932A CN102230786A (en) | 2011-03-31 | 2011-03-31 | Optical-measurement-based method for testing wall thickness of wax pattern for hollow turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102230786A true CN102230786A (en) | 2011-11-02 |
Family
ID=44843377
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100801932A Pending CN102230786A (en) | 2011-03-31 | 2011-03-31 | Optical-measurement-based method for testing wall thickness of wax pattern for hollow turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102230786A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104457501A (en) * | 2014-11-29 | 2015-03-25 | 无锡透平叶片有限公司 | Method for rapidly detecting thickness size of section of vane |
| CN109685890A (en) * | 2018-12-24 | 2019-04-26 | 厦门大学 | A kind of hollow turbine vane film cooling holes back wall damage active protection method |
| CN110686605A (en) * | 2019-10-11 | 2020-01-14 | 成都飞机工业（集团）有限责任公司 | Non-contact composite part thickness measuring 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 |
| CN113721233A (en) * | 2021-08-30 | 2021-11-30 | 中国航发沈阳黎明航空发动机有限责任公司 | Three-dimensional optical measurement method for thermal barrier coating thickness of guide blade of multi-connected turbine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6709237B2 (en) * | 2001-03-26 | 2004-03-23 | Siemens Aktiengesellschaft | Turbine blade or vane and process for producing a turbine blade or vane |
| US7458411B2 (en) * | 2004-11-26 | 2008-12-02 | Snecma | Method for manufacturing cast ceramic cores for turbomachine blades |
| CN101907439A (en) * | 2010-03-17 | 2010-12-08 | 中国二十二冶集团有限公司 | Stimulated measurement and detection method in architectural steel structure fabrication |
-
2011
- 2011-03-31 CN CN2011100801932A patent/CN102230786A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6709237B2 (en) * | 2001-03-26 | 2004-03-23 | Siemens Aktiengesellschaft | Turbine blade or vane and process for producing a turbine blade or vane |
| US7458411B2 (en) * | 2004-11-26 | 2008-12-02 | Snecma | Method for manufacturing cast ceramic cores for turbomachine blades |
| CN101907439A (en) * | 2010-03-17 | 2010-12-08 | 中国二十二冶集团有限公司 | Stimulated measurement and detection method in architectural steel structure fabrication |
Non-Patent Citations (3)
| Title |
|---|
| 徐岳琳 等: "内切圆弦长法计算空心涡轮叶片蜡模壁厚", 《航空学报》 * |
| 黄胜利 等: "基于主动轮廓模型的复杂陶芯弯扭变形分析", 《计算机集成制造系统》 * |
| 龚正国 等: "基于光学扫描测量数据的叶片型面偏差分析研究", 《现代制造工程》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104457501A (en) * | 2014-11-29 | 2015-03-25 | 无锡透平叶片有限公司 | Method for rapidly detecting thickness size of section of vane |
| CN104457501B (en) * | 2014-11-29 | 2017-07-28 | 无锡透平叶片有限公司 | A kind of method of quick detection blade sectional thickness size |
| CN109685890A (en) * | 2018-12-24 | 2019-04-26 | 厦门大学 | A kind of hollow turbine vane film cooling holes back wall damage active protection method |
| CN110686605A (en) * | 2019-10-11 | 2020-01-14 | 成都飞机工业（集团）有限责任公司 | Non-contact composite part thickness measuring method |
| CN110686605B (en) * | 2019-10-11 | 2021-09-07 | 成都飞机工业（集团）有限责任公司 | Non-contact composite part thickness measuring 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 |
| CN111259557B (en) * | 2020-01-21 | 2022-05-20 | 山西大学 | Hollow turbine blade wall thickness deviation reverse regulation and control method based on ceramic core positioning compensation |
| CN113721233A (en) * | 2021-08-30 | 2021-11-30 | 中国航发沈阳黎明航空发动机有限责任公司 | Three-dimensional optical measurement method for thermal barrier coating thickness of guide blade of multi-connected turbine |
| CN113721233B (en) * | 2021-08-30 | 2023-09-19 | 中国航发沈阳黎明航空发动机有限责任公司 | Three-dimensional optical measurement method for thickness of thermal barrier coating of multi-body turbine guide vane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103644860B (en) | Large space free curved face measurement method | |
| CN100538261C (en) | Unknown free curved face self-adapting measuring method and gauge head unit based on the method for exploring the way | |
| CN102135417B (en) | Full-automatic three-dimension characteristic extracting method | |
| CN102735204B (en) | Chord-line-based aviation thin-wall blade machining torsion degree error measurement method | |
| CN102230786A (en) | Optical-measurement-based method for testing wall thickness of wax pattern for hollow turbine blade | |
| WO2023060683A1 (en) | Three-dimensional point cloud model-based method for measuring surface flatness of prefabricated beam segment | |
| CN103942837B (en) | The direct building method of blade point cloud model cross section curve based on Successive linear programming | |
| CN103777570A (en) | Machining error rapid detection and compensation method based on NURBS curved surface | |
| CN102735175B (en) | A kind of method based on Moving Least determination maximum blade thickness | |
| CN102661699A (en) | Precision measurement method of large-radius short arc part | |
| CN108682043A (en) | A kind of complex-curved measure planning method based on parameter mapping | |
| CN104089599B (en) | Quasi morphological filtering method for extracting two-dimensional contour in contact measuring head measurement | |
| CN112461175A (en) | Method for measuring wide chord and large torsion angle blade profile of fan blisk | |
| CN107330142A (en) | A kind of measuring point method arrow evaluation method of On-machine Test based on STL models | |
| WO2021139485A1 (en) | Ridge line damage extent measurement method and apparatus therefor | |
| CN107806836A (en) | A kind of finish forge blade profile detection method based on five-axle linkage spot light | |
| CN108073747A (en) | Aircraft structure Three Dimensional Design Model quality detecting system and method | |
| CN106767505A (en) | The MBD measurement techniques of large-scale multiple material high accuracy difficult point part | |
| CN109531273A (en) | A kind of casting bay section processing method based on precise detection technology | |
| CN109858124A (en) | A kind of measurement of blade of aviation engine and stock removal calculation method | |
| CN109059821A (en) | Coordinate measuring machine measurement path planning method | |
| CN104462807A (en) | Blade type value checking method for precision casting type spray pushing impeller | |
| CN105588512B (en) | The measuring device and method of class rectangle tunnel tunnel segment component size | |
| CN108161660A (en) | A kind of generation method of polish work station and its machining locus | |
| CN102147221A (en) | Three-coordinate measuring method of blade with T-shaped root |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20111102 |