CN117314997A - Propeller blade processing parameter measurement method - Google Patents

Propeller blade processing parameter measurement method Download PDF

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Publication number
CN117314997A
CN117314997A CN202311290758.9A CN202311290758A CN117314997A CN 117314997 A CN117314997 A CN 117314997A CN 202311290758 A CN202311290758 A CN 202311290758A CN 117314997 A CN117314997 A CN 117314997A
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China
Prior art keywords
line
blade
propeller
center
pressure surface
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Pending
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CN202311290758.9A
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Chinese (zh)
Inventor
朱晶
孙赫应
于霄雷
陈秋实
修世强
吴宣胜
胡南
张桐宇
张君
程仕李
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DALIAN MARINE PROPELLER CO LTD
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DALIAN MARINE PROPELLER CO LTD
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Priority to CN202311290758.9A priority Critical patent/CN117314997A/en
Publication of CN117314997A publication Critical patent/CN117314997A/en
Pending legal-status Critical Current

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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T7/00—Image analysis
    • G06T7/60—Analysis of geometric attributes
    • 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
    • G01B21/02—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 length, width, or thickness
    • G01B21/08—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 length, width, or thickness for measuring thickness
    • 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
    • G01B21/10—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 diameters
    • 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
    • G01B21/22—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 angles or tapers; for testing the alignment of axes
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T7/00—Image analysis
    • G06T7/0002—Inspection of images, e.g. flaw detection
    • G06T7/0004—Industrial image inspection
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T7/00—Image analysis
    • G06T7/60—Analysis of geometric attributes
    • G06T7/62—Analysis of geometric attributes of area, perimeter, diameter or volume
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06V—IMAGE OR VIDEO RECOGNITION OR UNDERSTANDING
    • G06V30/00—Character recognition; Recognising digital ink; Document-oriented image-based pattern recognition
    • G06V30/40—Document-oriented image-based pattern recognition
    • G06V30/42—Document-oriented image-based pattern recognition based on the type of document
    • G06V30/422—Technical drawings; Geographical maps
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T2207/00—Indexing scheme for image analysis or image enhancement
    • G06T2207/30—Subject of image; Context of image processing
    • G06T2207/30108—Industrial image inspection
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06V—IMAGE OR VIDEO RECOGNITION OR UNDERSTANDING
    • G06V2201/00—Indexing scheme relating to image or video recognition or understanding
    • G06V2201/06—Recognition of objects for industrial automation

Abstract

The invention relates to a propeller blade processing parameter measurement method which comprises the steps of establishing a propeller three-dimensional model, obtaining a bottom view of the three-dimensional model, restoring and drawing a two-dimensional bottom view according to bottom view data 1:1, determining a reference datum line, determining a datum angle, obtaining an angle value and a radius value required by processing, restoring the obtained angle into the three-dimensional model, obtaining a height value required by processing, and finally obtaining processing parameters of all blades. According to the invention, through the conversion of the three-dimensional model and the two-dimensional bottom view, the radius, the angle and the height required by processing can be accurately obtained under the condition that only rectangular coordinate data is given on a drawing; the rectangular coordinate design scheme of the given propeller can be converted into a propeller manufacturing process method matched with the cylindrical coordinates, the difficulty is reduced, and the conventional equipment resources are utilized for measurement and processing, so that the smooth manufacturing of the propeller is realized.

Description

Propeller blade processing parameter measurement method
Technical Field
The invention relates to the technical field of propeller manufacturing, in particular to a propeller blade processing parameter measurement method.
Background
The propeller is a revolution body with irregular complex curved blades, and the manufacturing precision requirement is extremely high. The general design drawing lists the main parameter values such as the section radius value, the pitch angle, the blade thickness and the like according to the data mode of the cylindrical coordinates, and along with the improvement of the propeller design technology and the update of the design concept, more and more design units directly provide the designed propeller products with the design parameters of a rectangular coordinate system to a propeller manufacturing company, so that the manufacturing company cannot intuitively obtain the processing parameters.
Disclosure of Invention
The invention provides a propeller blade processing parameter measuring method, which aims to solve the technical problem that in the prior art, a propeller processing parameter cannot be obtained according to rectangular coordinate system data.
The technical scheme adopted by the invention for achieving the purpose is as follows: a propeller blade processing parameter measurement method comprises the following steps:
s1: establishing a propeller three-dimensional model according to the hub, the blade position data and the pitch of a rectangular coordinate system of a design drawing;
s2: obtaining a bottom view of the three-dimensional model;
s3: position data are obtained from the bottom view of the three-dimensional model, and two-dimensional software is used for restoring and drawing the two-dimensional bottom view according to the proportion of 1:1;
s4: determining a reference datum line;
s5: determining a reference angle;
s6: acquiring an angle value and a radius value required by processing;
s7: restoring the obtained angle value and radius value into a three-dimensional model;
s8: obtaining a height value required by processing;
s9: repeating the steps S1-S8 to obtain the processing parameters of each blade on the propeller;
preferably, the step S3 specifically includes: selecting a bottom view mode of a three-dimensional model in three-dimensional drawing software, projecting a propeller blade pressure surface into a plane graph, using a measuring tool carried by the software to obtain position data of a blade tip, a propeller tip circle, a propeller hub small end surface center point, a blade pressure surface center line, a blade pressure surface trailing edge line and a blade pressure surface leading edge line, wherein the position of the blade tip is a blade datum point (0, 0) coordinate position, and according to the position data obtained in the step S2, using two-dimensional drawing software to restore and draw a propeller blade pressure surface two-dimensional graph according to a 1:1 ratio;
preferably, the step S4 refers to the reference line obtaining method specifically including: in the two-dimensional diagram of the propeller blade pressure surface obtained in the step S3, the small end face of the propeller hub is taken as a reference surface, the blade tip position is determined, namely, the coordinate position of a blade reference point (0, 0) is obtained, and the center point of the small end face of the propeller hub and the blade tip are connected to form a reference line;
preferably, the determining of the reference angle in step S5 specifically includes: the center point of the small end surface is taken as a starting point, a straight line is tangent to the thickness center line of the trailing edge of the pressure surface of the blade, a positioning datum line is obtained, and an included angle between the positioning datum line and the reference datum line is taken as a datum angle;
preferably, the step S6 specifically includes the following steps:
s6.1: marking rectangular coordinate section position lines of the blade according to rectangular coordinate system data of a design drawing by taking a small end face of a hub as a reference plane in a two-dimensional graph to obtain a first intersection point of the section position lines and trailing edge lines of the blade pressure surface, a second intersection point of the section position lines and a central line of the blade pressure surface and a third intersection point of the section position lines and leading edge lines of the blade pressure surface;
s6.2: connecting a small end surface center point of the propeller hub with a first intersection point to obtain a random intersection line;
s6.3: connecting the center point of the small end surface of the propeller hub with the second intersection point to obtain a center intersection line;
s6.4: connecting the center point of the small end surface of the propeller hub with a third intersection point to obtain a guiding edge intersection line;
s6.5: acquiring a trailing edge included angle between the positioning datum line and a trailing edge intersection line and a center included angle between the positioning datum line and a center intersection line, measuring and recording the trailing edge included angle, the center included angle and the angle of the leading edge included angle;
s6.6: the center point of the small end surface of the propeller hub is used as a circle center to make a circle, the circle is intersected with the trailing edge line of the pressure surface of the propeller blade at a first intersection point, and the radius of the circle is the radius of the trailing edge of the pressure surface of the propeller blade;
s6.7: the center point of the small end surface of the hub is used as the center of a circle, and the center point of the small end surface of the hub is intersected with the center line of the blade at a second intersection point, and the radius of the circle is the position radius of the center line measuring point of the pressure surface of the blade;
s6.8: the center point of the small end surface of the propeller hub is used as a circle center to make a circle, and the circle is intersected with the edge line of the leading edge of the pressure surface of the propeller blade at a third intersection point, and the radius of the circle is the radius of the edge position of the leading edge of the pressure surface of the propeller blade;
preferably, the step S8 includes the steps of:
s8.1: selecting a rear view mode from the three-dimensional model obtained in the step S7, taking a first intersection point of the trailing edge line of the blade pressure surface and the circle in the step S6.6 as a vertex, and making a vertical line to the small end surface of the hub to obtain the trailing edge position height of the blade pressure surface;
s8.2: taking the second intersection point of the center line of the blade pressure surface and the circle in S6.7 as a vertex, and making a vertical line to the small end surface of the hub to obtain the position height of the center line of the blade;
s8.3: and (3) taking the third intersection point of the edge line of the blade pressure surface edge and the circle in S6.8 as a vertex, and making a vertical line to the small end face of the hub to obtain the position height of the blade pressure surface edge.
Compared with the prior art, the invention has the beneficial effects that the radius, the angle and the height required by processing can be accurately obtained under the condition that only rectangular coordinate data is given by a drawing through the conversion of a three-dimensional model and a two-dimensional bottom view; the rectangular coordinate design scheme of the given propeller can be converted into a propeller manufacturing process method matched with the cylindrical coordinates, the difficulty is reduced, and the conventional equipment resources are utilized for measurement and processing, so that the smooth manufacturing of the propeller is realized.
Drawings
FIG. 1 is a flow chart of the method of the present invention.
Fig. 2 is a two-dimensional bottom view of a propeller as measured by the present invention.
Fig. 3 is a rear view of a three-dimensional model of a propeller as measured by the present invention.
In the figure: 1: propeller blade pressure surfaces; 2: a blade tip; 3: tip circle of the propeller; 4: small end face of propeller hub; 5: the center point of the small end surface of the propeller hub; 6: a blade pressure face centerline; 7: blade pressure surface trailing edge line; 8: blade pressure surface leading edge line; 9: referring to the datum line; 10: positioning a datum line; 11: a reference angle; 12: a section position line; 13: a first intersection point; 14: a second intersection point; 15: a third intersection point; 16: intersecting the line along with the edge; 17: a central intersecting line; 18: edge guiding intersecting lines; 19: included angles along with the edges; 20: a center included angle; 21: an included angle of the guide edge; 22: radius of the blade pressure surface along with the edge position; 23: the position radius of the center line measuring point of the blade pressure surface; 24: the radius of the edge of the leading edge of the pressure surface of the blade; 25: the height of the trailing edge of the blade pressure surface; 26: the position height of the center line of the blade; 27: blade pressure face leading edge position height.
Detailed Description
The invention discloses a propeller blade processing parameter measurement method, which comprises the following steps of:
s1: according to the position data and the pitch of the propeller hub and the propeller blade provided by the rectangular coordinate system of the design drawing, a propeller three-dimensional model is built in UG software;
s2: obtaining a bottom view of the three-dimensional model;
s3: position data are obtained from the bottom view of the three-dimensional model, and CAD drawing software is used for restoring and drawing a two-dimensional bottom view according to the proportion of 1:1; the method comprises the following steps: selecting a bottom view mode of a three-dimensional model in UG software, projecting a propeller blade pressure surface 1 into a plane graph, using a measuring tool carried by the software to obtain position data of a blade tip 2, a propeller tip circle 3, a propeller hub small end surface 4, a propeller hub small end surface center point 5, a blade pressure surface center line 6, a blade pressure surface trailing edge line 7 and a blade pressure surface leading edge line 8, wherein the position of the blade tip 2 is the coordinate position of a blade datum point (0, 0), and according to the position data obtained in S2, using CAD drawing software to restore and draw a propeller blade pressure surface 1 two-dimensional graph according to a 1:1 proportion;
s4: the reference datum line is determined, specifically: in the two-dimensional diagram of the propeller blade pressure surface obtained in the step S3, the small end surface 4 of the propeller hub is taken as a reference surface, the position of the blade tip 2 is determined, namely, the coordinate position of a blade datum point (0, 0) is obtained, and the center point 5 of the small end surface of the propeller hub is connected with the blade tip 2 to form a reference datum line 9;
s5: the reference angle is determined, specifically: taking a small end face center point 5 as a starting point, making a straight line tangent to the thickness center line of the blade pressure surface along with the edge to obtain a positioning datum line 10, wherein an included angle between the positioning datum line 10 and a reference datum line 9 is a datum angle 11;
s6: the method for acquiring the angle value and the radius value required by processing specifically comprises the following steps:
s6.1: in a two-dimensional diagram, a small end face 4 of a propeller hub is taken as a reference plane, a section with a certain distance from a propeller blade tip 2 is determined according to rectangular coordinate system data of a design drawing, a rectangular coordinate section position line 12 of a blade is marked according to position data of the section in a rectangular coordinate system, and a first intersection point 13 of the section position line 12 and a trailing edge line 7 of a blade pressure surface, a second intersection point 14 of the section position line 12 and a central line 6 of the blade pressure surface and a third intersection point 15 of the section position line 12 and a leading edge line 8 of the blade pressure surface are obtained;
s6.2: connecting the center point 5 of the small end surface of the hub with the first intersection point 13 to obtain a random intersection line 16;
s6.3: connecting the center point 5 of the small end surface of the hub with the second intersection point 14 to obtain a center intersection line 17;
s6.4: connecting the center point 5 of the small end surface of the hub with a third intersection point 15 to obtain a leading edge intersection line 18;
s6.5: obtaining a trailing edge included angle 19 between the positioning datum line 10 and the trailing edge intersection line 16 and a center included angle 20 between the positioning datum line 10 and the center intersection line 17, and measuring and recording the angles of the trailing edge included angle 19, the center included angle 20 and the leading edge included angle 21, wherein the leading edge included angle 21 is between the positioning datum line 10 and the leading edge intersection line 18;
s6.6: the center point 5 of the small end surface of the hub is used as a circle center to make a circle, and the circle intersects with the trailing edge line 7 of the pressure surface of the blade at a first intersection point 13, and the radius of the circle is the trailing edge position radius 22 of the pressure surface of the blade;
s6.7: the center point 5 of the small end surface of the hub is used as a circle center to make a circle, and the circle intersects with the center line 6 of the blade at a second intersection point 14, and the radius of the circle is the position radius 23 of the center line measuring point of the pressure surface of the blade;
s6.8: the center point 5 of the small end surface of the hub is used as a circle center to make a circle, and the circle intersects with the edge line 8 of the leading edge of the pressure surface of the blade at a third intersection point 15, and the radius of the circle is the radius 24 of the edge position of the leading edge of the pressure surface of the blade;
s7: restoring the obtained angle value and the radius value into the three-dimensional model, namely restoring and drawing the angle value and the radius value obtained in the two-dimensional bottom view in a bottom view mode of the three-dimensional model in a ratio of 1:1;
s8: the method for obtaining the height value required by processing specifically comprises the following steps:
s8.1: selecting a rear view mode from the three-dimensional model obtained in the step S7, taking a first intersection point 13 of the blade pressure surface trailing edge line 7 and a circle in the step S6.6 as a vertex, and making a vertical line to the small end surface 4 of the hub to obtain the blade pressure surface trailing edge position height 25;
s8.2: taking the second intersection point 14 of the center line 6 of the blade pressure surface and the circle in S6.7 as a vertex, and making a vertical line to the small end surface 4 of the hub to obtain the position height 26 of the center line of the blade;
s8.3: and taking a third intersection point 15 of the blade pressure surface leading edge line 8 and the circle in S6.8 as a vertex, and making a vertical line to the small end surface 4 of the hub to obtain the blade pressure surface leading edge position height 27.
S9: repeating the steps S1-S8 to obtain the processing parameters of each blade on the propeller, and applying the processing parameters to processing.
The present invention has been described in terms of embodiments, and it will be appreciated by those of skill in the art that various changes can be made to the features and embodiments, or equivalents can be substituted, without departing from the spirit and scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.

Claims (6)

1. The propeller blade processing parameter measurement method is characterized by comprising the following steps of:
s1: establishing a propeller three-dimensional model according to the hub, the blade position data and the pitch of a rectangular coordinate system of a design drawing;
s2: obtaining a bottom view of the three-dimensional model;
s3: position data are obtained from the bottom view of the three-dimensional model, and two-dimensional software is used for restoring and drawing the two-dimensional bottom view according to the proportion of 1:1;
s4: determining a reference datum line;
s5: determining a reference angle;
s6: acquiring an angle value and a radius value required by processing;
s7: restoring the obtained angle value and radius value into a three-dimensional model;
s8: obtaining a height value required by processing;
s9: repeating the steps S1-S8 to obtain the processing parameters of each blade on the propeller.
2. The method for measuring the processing parameters of the propeller blade according to claim 1, wherein the step S3 specifically comprises: selecting a bottom view mode of a three-dimensional model in three-dimensional drawing software, projecting a propeller blade pressure surface (1) into a plane graph, using a measuring tool carried by the software to obtain the position data of a blade tip (2), a propeller tip circle (3), a propeller hub small end surface (4), a propeller hub small end surface center point (5), a blade pressure surface center line (6), a blade pressure surface trailing edge line (7) and a blade pressure surface leading edge line (8), wherein the position of the blade tip (2) is the coordinate position of a blade datum point (0, 0), and according to the position data obtained in the S2, using two-dimensional drawing software to restore and draw a two-dimensional graph of the propeller blade pressure surface (1) according to a 1:1 ratio.
3. The method for measuring the processing parameters of the propeller blade according to claim 2, wherein the step S4 is specifically a method for obtaining the reference line by referring to the reference line, comprising the following steps: in the two-dimensional diagram of the propeller blade pressure surface obtained in the step S3, the small end surface (4) of the propeller hub is taken as a reference surface, the position of the blade tip (2) is determined, namely, the coordinate position of a blade datum point (0, 0) is obtained, and the center point (5) of the small end surface of the propeller hub and the blade tip (2) are connected to form a reference datum line (9).
4. A method for measuring a processing parameter of a propeller blade according to claim 3, wherein the determining of the reference angle in step S5 specifically includes: and (3) taking a small end face center point (5) as a starting point, making a straight line tangent to the thickness center line of the blade pressure surface along with the edge to obtain a positioning datum line (10), and taking an included angle between the positioning datum line (10) and the reference datum line (9) as a datum angle (11).
5. The method for measuring the processing parameters of the propeller blade according to claim 4, wherein the step S6 specifically comprises the following steps:
s6.1: marking a rectangular coordinate section position line (12) of the blade according to rectangular coordinate system data of a design drawing by taking a small end surface (4) of a blade hub as a reference surface in a two-dimensional diagram to obtain a first intersection point (13) of the section position line (12) and a trailing edge line (7) of a blade pressure surface, a second intersection point (14) of the section position line (12) and a central line (6) of the blade pressure surface and a third intersection point (15) of the section position line (12) and a leading edge line (8) of the blade pressure surface;
s6.2: connecting a small end surface center point (5) of the propeller hub with a first intersection point (13) to obtain a random intersection line (16);
s6.3: connecting a center point (5) of the small end surface of the propeller hub with a second intersection point (14) to obtain a center intersection line (17);
s6.4: connecting a center point (5) of the small end surface of the hub with a third intersection point (15) to obtain a guiding edge intersection line (18);
s6.5: obtaining a trailing edge included angle (19) between the positioning datum line (10) and the trailing edge intersection line (16), and a center included angle (20) between the positioning datum line (10) and the center intersection line (17), and measuring and recording the angles of the trailing edge included angle (19), the center included angle (20) and the leading edge included angle (21) by the guiding edge included angle (21) between the positioning datum line (10) and the leading edge intersection line (18);
s6.6: taking a center point (5) of a small end surface of a hub as a circle center, and intersecting with a trailing edge line (7) of a blade pressure surface at a first intersection point (13), wherein the radius of the circle is the trailing edge position radius (22) of the blade pressure surface;
s6.7: taking a center point (5) of a small end surface of the hub as a circle center, and intersecting with a blade center line (6) at a second intersection point (14), wherein the radius of the circle is the position radius (23) of a blade pressure surface center line measuring point;
s6.8: and (3) taking the center point (5) of the small end surface of the hub as a circle center, and intersecting with the edge line (8) of the leading edge of the pressure surface of the blade at a third intersection point (15), wherein the radius of the circle is the radius (24) of the edge of the leading edge of the pressure surface of the blade.
6. A method for measuring a processing parameter of a propeller blade according to claim 1, wherein said step S8 comprises the steps of:
s8.1: selecting a rear view mode from the three-dimensional model obtained in the step S7, taking a first intersection point (13) of a blade pressure surface trailing edge line (7) and a circle in the step S6.6 as a vertex, and making a vertical line to a small end surface (4) of the hub to obtain the blade pressure surface trailing edge position height (25);
s8.2: taking a second intersection point (14) of the center line (6) of the blade pressure surface and the circle in S6.7 as an apex, and making a vertical line to the small end surface (4) of the hub to obtain the position height (26) of the center line of the blade;
s8.3: and taking a third intersection point (15) of the blade pressure surface edge guiding line (8) and the circle in S6.8 as a vertex, and making a vertical line to the small end surface (4) of the hub to obtain the blade pressure surface edge guiding edge position height (27).
CN202311290758.9A 2023-10-08 2023-10-08 Propeller blade processing parameter measurement method Pending CN117314997A (en)

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Application Number Priority Date Filing Date Title
CN202311290758.9A CN117314997A (en) 2023-10-08 2023-10-08 Propeller blade processing parameter measurement method

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