CN113204871A - Aviation blade air film hole identification method, device and system - Google Patents
Aviation blade air film hole identification method, device and system Download PDFInfo
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Abstract
The invention discloses a method, a device and a system for identifying an aviation blade air film hole, belonging to the field of aviation blade detection, wherein the method further comprises the following steps: s1: carrying out curvature calculation on original measuring points on blade profile measuring points in the aviation blade with the air film holes to obtain curvature distribution of the blade profile measuring points; determining a curvature mutation area on a leaf profile measuring point based on a curvature threshold and curvature distribution; s2: pre-matching the leaf profile measuring points and the theoretical leaf profile, and establishing a nearest K distance data structure corresponding to the leaf profile measuring points and the theoretical leaf profile; s3: searching possible air film hole measuring points on the profile measuring points of the theoretical blade profile from the nearest K distance data structure based on the position size threshold of the theoretical air film hole in the theoretical blade profile; s4: and determining the actual gas film hole measuring point from the possible gas film hole measuring points according to the position relation between the possible gas film hole measuring points and the curvature mutation areas of the leaf profile measuring points. The method can improve the identification efficiency of the air film hole and the qualification rate of the aviation blade.
Description
Technical Field
The invention belongs to the field of aviation blade detection, and particularly relates to an aviation blade air film hole identification method, device and system.
Background
The aircraft engine is regarded as an industrial product with the most complex structure and the highest technical threshold in the world, and is always known as a bright bead on an industrial crown, and the aircraft blade is used as a core component of the aircraft engine, which directly influences the pneumatic performance of the aircraft engine, so that the accurate profile quality control of the aircraft engine is particularly important. Based on the consideration of exhaust performance, the existing aviation blade adopts a design mode of increasing an air film hole on a blade body, however, the air film hole design brings new errors to the blade profile analysis and evaluation work based on three-coordinate measurement.
The existing aviation multi-connected blade detection process often misjudges an air film hole measuring point as a profile tolerance point, so that the air film hole identification efficiency is low, and the aviation blade qualification rate is reduced.
Disclosure of Invention
Aiming at the defects or improvement requirements of the prior art, the invention provides an identification method, device and system of an aviation blade air film hole, and aims to search out a possible air film hole measuring point from a nearest K-distance data structure based on a position size threshold of a theoretical air film hole, and further determine an actual air film hole measuring point according to the position relation between the possible air film hole measuring point and a curvature mutation area of a blade profile measuring point, so that the technical problems of low air film hole identification efficiency and low aviation blade qualification rate in the prior art are solved.
To achieve the above object, according to one aspect of the present invention, there is provided an identification method of an aviation blade air film hole, including:
s1: carrying out curvature calculation on original measuring points on blade profile measuring points in an aviation blade with air film holes to obtain curvature distribution of the blade profile measuring points; determining a curvature mutation area on the leaf profile measuring point based on a curvature threshold and the curvature distribution;
s2: pre-matching the blade profile measuring points with a theoretical blade profile, and establishing a nearest K distance data structure corresponding to the blade profile measuring points and the theoretical blade profile;
s3: searching possible air film hole measuring points on the blade profile contour measuring points from the nearest K-distance data structure based on the position size threshold of the theoretical air film holes in the theoretical blade profile;
s4: and determining an actual air film hole measuring point from the possible air film hole measuring points according to the position relation between the possible air film hole measuring points and the curvature mutation areas of the leaf profile measuring points.
In one embodiment, the S1 includes:
s11: interpolating the leaf profile measuring points by adopting a cubic spline curve, and encrypting the original measuring points on the spline curve to obtain encrypted measuring points; by using
Calculating a curvature value of each encrypted measuring point, wherein x (u) and y (u) represent measuring point coordinates of each spline curve segment in a node vector u after encryption, and u is more than or equal to 0 and less than or equal to 1;
s12: calculating the average value of the curvature values of the encrypted measuring points and the original measuring points, and drawing a curvature distribution curve;
s13: in the curvature distribution curve, a region composed of the encrypted measuring point with the curvature value larger than the curvature threshold value and the adjacent original measuring point is regarded as the curvature abrupt change region.
In one embodiment, the process of cubic spline curve interpolation is as follows:
all original measuring points { P ] on the leaf profile measuring points1,P2,P3,…,PmTaking the m +2 control points (B) containing the head and tail control points as type value points, and solving the m +2 control points containing the head and tail control points by inverting the type value points1,B2,B3,…,Bm+2}，
Wherein the coordinates P of the measuring points are encryptedj′＝R3·uj 3+R2·uj 2+R1·uj 1+R0，j∈[1,m-1]；R0、R1、R2、R3Calculated from the m +2 control points.
In one embodiment, the S2 includes:
copy the original site { P }0,P1,P2,…,PmGetTo a moving measurement point { P0′,P1′,P2′,…,Pm' }, calculating the moving measuring points and the theoretical leaf profile by using a VMM algorithm to obtain a transformation matrix T, and enabling the moving measuring points to meet the theoretical leaf profile distance and the minimum matching position to obtain matching measuring points { P }0″,P1′,′P2″,…,Pm″}；
Establishing theoretical leaf profile measuring point { L0,L1,L2,…,LwTo said match measurement point { P }0″,P1′,′P2″,…,PmMapping structure of nearest neighbor of "; measuring point L for each of said theoretical blade profilesiThere are indices for the nearest K matching stations each I0,I1,I2,…,Ik}。
In one embodiment, the S3 includes:
a circular area is defined by taking the air film hole coordinate of the theoretical blade profile as the center of a circle, giving a diameter D and an amplification factor alpha
The coordinate distance of the air mold hole in the nearest K distance data structure
The leaf profile measurement points of (a) are considered the possible gas film hole measurement points.
In one embodiment, the curvature values of the possible gas film hole measuring points are compared;
if the possible gas film hole measuring point P is located in the curvature mutation area, the possible gas film hole measuring point P is regarded as the actual gas film hole measuring point;
and if the possible gas film hole measuring point Q is positioned outside the curvature mutation region, the point is regarded as a normal point, and the point which is not regarded as the actual gas film hole measuring point in the curvature mutation region is judged as a blade machining error point.
According to another aspect of the invention, an identification device for an aviation blade air film hole is provided, which comprises:
the calculation module is used for carrying out curvature calculation on original measuring points on blade profile measuring points in the aviation blade with the air film holes to obtain curvature distribution of the blade profile measuring points; determining a curvature mutation area on the leaf profile measuring point based on a curvature threshold and the curvature distribution;
the establishing module is used for pre-matching the blade profile measuring points with a theoretical blade profile and establishing a nearest K distance data structure corresponding to the blade profile measuring points and the theoretical blade profile;
the searching module is used for searching possible air film hole measuring points on the blade profile contour measuring points from the nearest K-distance data structure by utilizing the position size threshold of the theoretical air film hole in the theoretical blade profile;
and the determining module is used for determining an actual gas film hole measuring point from the possible gas film hole measuring points according to the position relation between the possible gas film hole measuring points and the curvature mutation areas of the leaf profile measuring points.
According to another aspect of the invention, an identification system for an aviation blade film hole is provided, which comprises: the aviation blade film hole identification method comprises a memory and a processor, wherein a computer program is stored in the memory, and when the computer program is executed by the processor, the processor executes the steps of the aviation blade film hole identification method.
Generally, compared with the prior art, the above technical solution conceived by the present invention has the following beneficial effects:
(1) the method carries out curvature calculation on all points of the blade profile measuring points of the aviation blade with the air film holes to obtain the curvature distribution of the blade profile measuring points. And determining a curvature abrupt change region on a leaf profile measuring point according to a set curvature threshold value. And pre-matching the leaf profile measuring point and the theoretical leaf profile by adopting a VMM algorithm, and establishing a data structure of the nearest K distance between the leaf profile measuring point and the theoretical leaf profile. And searching possible air film hole measuring points of the blade profile measuring points within the range according to the given circle center position and diameter of the theoretical air film hole in the theoretical blade profile and the data structure of the nearest K distance between the blade profile measuring point and the theoretical blade profile. And regarding possible air film hole measuring points of the leaf profile measuring points within the range, according to the curvature mutation areas of the comparison leaf profile measuring points, the leaf profile measuring points which meet the conditions within the range of the curvature mutation and the theoretical air film hole are regarded as the air film hole measuring points. The method can improve the identification efficiency of the air film hole and the qualification rate of the aviation blade, and the subsequent matching evaluation work is preprocessed.
(2) The invention adopts a spline curve mode when calculating the curvature, increases the density of points and solves the problem of larger plane curvature calculation error fluctuation caused by insufficient measuring points of the cross section profile.
(3) The method and the device mainly adopt two modes of curvature identification and template matching to judge the air film hole at the same time, distinguish the actual air film hole from the actual processing groove, and improve the accuracy of air film hole identification.
Drawings
FIG. 1 is a flow chart of a method for identifying an aviation blade film hole in accordance with an embodiment of the present invention;
FIG. 2 is a flow chart of a method for identifying an aero blade film hole in accordance with another embodiment of the present invention;
FIG. 3 is a curvature profile of a cross-sectional profile of a hole with a film in accordance with an embodiment of the present invention;
FIG. 4 is a comparison graph of the effects before and after the identification and deletion of the air film holes in one embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
As shown in fig. 1, there is provided a method for identifying an aviation blade film hole, including:
s1: carrying out curvature calculation on original measuring points on blade profile measuring points in the aviation blade with the air film holes to obtain curvature distribution of the blade profile measuring points; determining a curvature mutation area on a leaf profile measuring point based on a curvature threshold and curvature distribution;
s2: pre-matching the leaf profile measuring points and the theoretical leaf profile, and establishing a nearest K distance data structure corresponding to the leaf profile measuring points and the theoretical leaf profile;
s3: searching possible air film hole measuring points on the profile measuring points of the theoretical blade profile from the nearest K distance data structure based on the position size threshold of the theoretical air film hole in the theoretical blade profile;
s4: and determining the actual gas film hole measuring point from the possible gas film hole measuring points according to the position relation between the possible gas film hole measuring points and the curvature mutation areas of the leaf profile measuring points.
Specifically, as shown in fig. 2, the identification method of the aviation blade air film hole provided by the invention comprises the following steps:
(1) and (3) carrying out curvature calculation on all points of the blade profile measuring points of the aviation blade with the air film holes to obtain the curvature distribution of the blade profile measuring points. And determining a curvature mutation area on the measuring point of the leaf profile according to the calculated curvature threshold value. Wherein, fig. 3 is a curvature distribution diagram of a cross-sectional profile with a gas film hole in an embodiment of the present invention, and the circle mark in the diagram represents a position with a larger absolute value of curvature, that is, a gas film hole measuring point of a blade measuring point profile.
(2) And pre-matching the leaf profile measuring point and the theoretical leaf profile by adopting a VMM algorithm, and establishing a data structure of the nearest K distance between the leaf profile measuring point and the theoretical leaf profile.
(3) And searching possible air film hole measuring points of the blade profile measuring points within the range according to the given circle center position and diameter of the theoretical air film hole in the theoretical blade profile and the data structure of the nearest K distance between the blade profile measuring point and the theoretical blade profile.
(4) And regarding possible air film hole measuring points of the leaf profile measuring points within the range, according to the curvature mutation areas of the comparison leaf profile measuring points, the leaf profile measuring points which meet the conditions within the range of the curvature mutation and the theoretical air film hole are regarded as the air film hole measuring points.
In the embodiment of the invention, the aviation blade profile contour measuring points are collected by a three-coordinate measuring machine, a point laser displacement sensor and an area array scanner, and the contour measuring points of the blade are given by coordinate information or control parameters of points, line segments, circular arcs and spline curves.
In one embodiment, S1 includes:
s11: interpolating the leaf profile measuring points by using a cubic spline curve, and encrypting the original measuring points on the spline curve to obtain encrypted measuring points; by using
Calculating the curvature value of each encrypted measuring point, wherein u is more than or equal to 0 and less than or equal to 1;
s12: calculating the average value of the curvature values of the encrypted measuring points and the curvature values of the original measuring points, and drawing a curvature distribution curve;
s13: in the curvature distribution curve, the region formed by the encrypted measuring point with the curvature value larger than the curvature threshold value and the adjacent original measuring point is regarded as a curvature abrupt change region.
Further, the specific way of curvature calculation is as follows:
interpolating the leaf profile measuring points by using a cubic spline curve, encrypting the measuring points on the spline curve, and obtaining P-R for each encrypted measuring point3·u3+R2·u2+R1·u1+R0The curvature calculation mode of the measuring point is as follows:
wherein x (u) and y (u) represent the coordinates of the measuring point of the node vector u after each spline curve is encrypted, and u is more than or equal to 0 and less than or equal to 1.
Further, the cubic spline curve interpolation mode is as follows: all the original measurement points { P }0,P1,P2,…,PmAs a type value point, performing inverse calculation to obtain m +2 control points (Q)0,Q1,Q2,…,Qm+2}。
Further, the specific implementation manner of the curvature distribution is as follows: and (4) counting the curvature values of all the encrypted measuring points and the curvature value of the original measuring point, calculating the average value of the two curvatures, and drawing a curvature distribution curve. And calculating the difference of the curvatures of the front and rear measuring points, and drawing a curvature difference curve.
Further, a curvature mutation region was obtainedThe method comprises the following steps: in the curvature distribution curve, the curvature is satisfied to be larger than the curvature threshold value kappaiAnd (5) encrypting the measuring point marks less than or equal to kappa, and regarding the original measuring point marks on two sides of the encrypted measuring points as curvature mutation areas. The curvature threshold κ is determined by the 3 σ rule from the gaussian distribution curve of curvature at each point.
In one embodiment, the process of cubic spline interpolation is: all original measuring points { P ] on the leaf profile measuring points1,P2,P3,…,PmTaking the m +2 control points { B } as norm points, and calculating m +2 control points by negating the norm points1,B2,B3,…,Bm+2Obtaining a spline curve; wherein, Pj＝R3·uj 3+R2·uj 2+R1·uj 1+R0，j∈(0，m)。
In one embodiment, the way to reverse the control point from the type point is:
all original measuring points { P ] on the leaf profile measuring points1,P2,P3,…,PmUsing the model value points as model value points to reversely calculate m +2 control points including head and tail control points { B }1,B2,B3,…,Bm+2Where B ═ A-1M, and
at the same time
In one embodiment, R0, R1, R2, R3 are calculated by the following formulas, respectively:
in one embodiment, S2 includes:
copy original measurement point { P }0,P1,P2,…,PmGet the mobile measurement point { P }0′,P1′,P2′,…,Pm' }, calculating the moving measuring points and the theoretical leaf profile by utilizing a VMM algorithm to obtain a transformation matrix T, and enabling the moving measuring points to meet the theoretical leaf profile distance and the minimum matching position to obtain matched measuring points { P }0″,P1′,′P2″,…,Pm″}；
Establishing theoretical leaf profile measuring point { L0,L1,L2,…,LwTo a matching station { P }0″,P1′,′P2″,…,PmMapping structure of nearest neighbor of "; for each theoretical leaf profile, measure point LiThere are indices for the nearest K matching stations each I0,I1,I2,…,Ik}。
Specifically, the VMM algorithm pre-matching mode is: the original measuring point data { P0,P1,P2,…,PmThe data of the mobile measuring point (P) is obtained by copying0′,P1′,P2′,…,Pm' }, calculating the data of the mobile measuring points and the theoretical blade profile of the cross section by a VMM algorithm to obtain a transformation matrix T, and transforming the data of the mobile measuring points to a matching position { P } which meets the distance between the mobile measuring points and the theoretical blade profile and is the minimum0″,P1′,′P2″,…,Pm″}。
Further, a data structure of the nearest K distance between the leaf profile survey point and the theoretical leaf profile is established in the following manner: establishing theoretical leaf profile { L0,L1,L2,…,LwTo the matched mobile station data { P }0″,P1′,′P2″,…,PmMapping structure of nearest neighbor of "", for each theoretical leaf profile measuring point LiThere are the nearest K indexes of the matched moving point data { I }0,I1,I2,…,Ik}。
In one embodiment, S3 includes:
air film with theoretical blade profileThe hole coordinate is used as the center of a circle, the given diameter D and the amplification factor alpha define a circular area
The nearest K is separated from the coordinate distance of the air mold hole in the data structure
The leaf profile measurement points of (a) are considered possible gas film hole measurement points.
In one embodiment, the curvature values of the possible gas film hole measuring points are compared; if the possible gas film hole measuring point P is located in the curvature mutation area, the possible gas film hole measuring point P is regarded as an actual gas film hole measuring point; and if the possible gas film hole measuring point Q is positioned outside the curvature mutation area, the point is regarded as a normal point, and the point which is not regarded as the actual gas film hole measuring point in the curvature mutation area is judged as a blade processing error point.
The method is suitable for profile segmentation of aviation multi-connected blade profiles in various forms. FIG. 4 is a comparison graph of the effects before and after the identification and deletion of the air film holes in one embodiment of the present invention. The left side is an effect diagram before the air film hole is deleted; the right side is an effect diagram after the air film holes are deleted, and the circle mark positions and the 101 mark positions are corresponding positions of the air film holes.
According to another aspect of the invention, an identification device for an aviation blade air film hole is provided, which comprises:
the calculation module is used for carrying out curvature calculation on original measuring points on blade profile measuring points in the aviation blade with the air film holes to obtain curvature distribution of the blade profile measuring points; determining a curvature mutation area on a leaf profile measuring point based on a curvature threshold and curvature distribution;
the establishing module is used for pre-matching the leaf profile measuring points and the theoretical leaf profile and establishing a nearest K distance data structure corresponding to the leaf profile measuring points and the theoretical leaf profile;
the searching module is used for searching possible air film hole measuring points on the profile measuring points of the theoretical blade profile from the nearest K distance data structure by utilizing the position size threshold of the theoretical air film hole in the theoretical blade profile;
and the determining module is used for determining the actual air film hole measuring point from the possible air film hole measuring points according to the position relation between the possible air film hole measuring points and the curvature mutation areas of the leaf profile measuring points.
According to another aspect of the invention, an identification system for an aviation blade film hole is provided, which comprises: the aviation blade air film hole identification method comprises a memory and a processor, wherein a computer program is stored in the memory, and when the computer program is executed by the processor, the processor executes the steps of the aviation blade air film hole identification method.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. An identification method for an aviation blade air film hole is characterized by comprising the following steps:
s1: carrying out curvature calculation on original measuring points on blade profile measuring points in an aviation blade with air film holes to obtain curvature distribution of the blade profile measuring points; determining a curvature mutation area on the leaf profile measuring point based on a curvature threshold and the curvature distribution;
s2: pre-matching the blade profile measuring points with a theoretical blade profile, and establishing a nearest K distance data structure corresponding to the blade profile measuring points and the theoretical blade profile;
s3: searching possible air film hole measuring points on the blade profile contour measuring points from the nearest K-distance data structure based on the position size threshold of the theoretical air film holes in the theoretical blade profile;
s4: and determining an actual air film hole measuring point from the possible air film hole measuring points according to the position relation between the possible air film hole measuring points and the curvature mutation areas of the leaf profile measuring points.
2. The identification method of an aviation blade film hole as claimed in claim 1, wherein said S1 includes:
s11: interpolating the leaf profile measuring points by adopting a cubic spline curve, and interpolating the leaf profile measuring points on the spline curveEncrypting the original measuring points to obtain encrypted measuring points; by using
Calculating a curvature value of each encrypted measuring point, wherein x (u) and y (u) represent measuring point coordinates of each spline curve segment in a node vector u after encryption, and u is more than or equal to 0 and less than or equal to 1;
s12: calculating the average value of the curvature values of the encrypted measuring points and the original measuring points, and drawing a curvature distribution curve;
s13: in the curvature distribution curve, a region composed of the encrypted measuring point with the curvature value larger than the curvature threshold value and the adjacent original measuring point is regarded as the curvature abrupt change region.
3. The identification method of an aviation blade film hole as claimed in claim 2, wherein the process of cubic spline curve interpolation is as follows:
all original measuring points { P ] on the leaf profile measuring points1,P2,P3,…,PmTaking the m +2 control points (B) containing the head and tail control points as type value points, and solving the m +2 control points containing the head and tail control points by inverting the type value points1,B2,B3,…,Bm+2Obtaining the spline curve;
wherein, the coordinate P 'of the measuring point is encrypted'j＝R3·uj 3+R2·uj 2+R1·uj 1+R0，j∈[1,m-1]；R0、R1、R2、R3Calculated from the m +2 control points.
4. The identification method of an aviation blade film hole as claimed in claim 3, wherein said S2 includes:
copy the original site { P }0,P1,P2,…,PmObtaining a mobile measuring point { P'0,P′1,P′2,…,P′mAnd calculating the mobile measuring points and the theoretical blade profiles by utilizing a VMM algorithm to obtain a transformation momentArray T, so that the moving measuring point meets the theoretical leaf profile distance and the minimum matching position to obtain a matching measuring point { P ″)0,P″1,P″2,…,P″m}；
Establishing theoretical leaf profile measuring point { L0,L1,L2,…,LwTo the matching measurement point { P ″)0,P″1,P″2,…,P″mMapping structure of nearest neighbourhood; measuring point L for each of said theoretical blade profilesiThere are indices for the nearest K matching stations each I0,I1,I2,…,Ik}。
5. The identification method of an aviation blade film hole as claimed in claim 1, wherein said S3 includes:
a circular area is defined by taking the air film hole coordinate of the theoretical blade profile as the center of a circle, giving a diameter D and an amplification factor alpha
The coordinate distance of the air mold hole in the nearest K distance data structure
The leaf profile measurement points of (a) are considered the possible gas film hole measurement points.
6. The identification method of an aviation blade film hole as claimed in claim 1, wherein said S4 includes:
comparing the curvature values of the possible gas film hole measuring points; if the possible gas film hole measuring point P is located in the curvature mutation area, the possible gas film hole measuring point P is regarded as the actual gas film hole measuring point;
and if the possible gas film hole measuring point Q is positioned outside the curvature mutation region, the point is regarded as a normal point, and the point which is not regarded as the actual gas film hole measuring point in the curvature mutation region is judged as a blade machining error point.
7. An identification device of aviation blade air film hole, characterized by includes:
the calculation module is used for carrying out curvature calculation on original measuring points on blade profile measuring points in the aviation blade with the air film holes to obtain curvature distribution of the blade profile measuring points; determining a curvature mutation area on the leaf profile measuring point based on a curvature threshold and the curvature distribution;
the establishing module is used for pre-matching the blade profile measuring points with a theoretical blade profile and establishing a nearest K distance data structure corresponding to the blade profile measuring points and the theoretical blade profile;
the searching module is used for searching possible air film hole measuring points on the blade profile contour measuring points from the nearest K-distance data structure by utilizing the position size threshold of the theoretical air film hole in the theoretical blade profile;
and the determining module is used for determining an actual gas film hole measuring point from the possible gas film hole measuring points according to the position relation between the possible gas film hole measuring points and the curvature mutation areas of the leaf profile measuring points.
8. An identification system for an aviation blade film hole, characterized by comprising a memory and a processor, wherein the memory stores a computer program, and the computer program, when executed by the processor, causes the processor to execute the steps of the identification method for an aviation blade film hole according to any one of claims 1 to 6.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115131334A (en) * | 2022-07-21 | 2022-09-30 | 北京汉飞航空科技有限公司 | Aviation engine pinhole type identification and automatic sequencing method based on machine learning |
| CN115130525A (en) * | 2022-07-21 | 2022-09-30 | 北京汉飞航空科技有限公司 | Automatic extraction method for digital-analog dustpan hole characteristics of engine turbine blade |
| CN116451156A (en) * | 2023-04-21 | 2023-07-18 | 中国科学院西安光学精密机械研究所 | Hole feature recognition method and sequencing method for blade air film holes |
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2021
- 2021-04-28 CN CN202110467995.2A patent/CN113204871A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115131334A (en) * | 2022-07-21 | 2022-09-30 | 北京汉飞航空科技有限公司 | Aviation engine pinhole type identification and automatic sequencing method based on machine learning |
| CN115130525A (en) * | 2022-07-21 | 2022-09-30 | 北京汉飞航空科技有限公司 | Automatic extraction method for digital-analog dustpan hole characteristics of engine turbine blade |
| CN115130525B (en) * | 2022-07-21 | 2023-04-07 | 北京汉飞航空科技有限公司 | Automatic extraction method for digital-analog dustpan hole characteristics of turbine blade of engine |
| CN116451156A (en) * | 2023-04-21 | 2023-07-18 | 中国科学院西安光学精密机械研究所 | Hole feature recognition method and sequencing method for blade air film holes |
| CN116451156B (en) * | 2023-04-21 | 2024-04-05 | 中国科学院西安光学精密机械研究所 | Hole feature recognition method and sequencing method for blade air film holes |
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