CN114252035B - Size detection method for turbine blade disc - Google Patents

Size detection method for turbine blade disc Download PDF

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Publication number
CN114252035B
CN114252035B CN202111311621.8A CN202111311621A CN114252035B CN 114252035 B CN114252035 B CN 114252035B CN 202111311621 A CN202111311621 A CN 202111311621A CN 114252035 B CN114252035 B CN 114252035B
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China
Prior art keywords
measured
points
turbine blade
throat
channel
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CN202111311621.8A
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Chinese (zh)
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CN114252035A (en
Inventor
杨中
杜应流
程雪松
董昌盛
潘飞翔
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Anhui Yingliu Hangyuan Power Technology Co Ltd
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Anhui Yingliu Hangyuan Power Technology Co Ltd
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    • 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
    • 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
    • G01B21/10—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
    • G01B21/14—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 internal 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
    • G01B21/28—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 areas

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • General Life Sciences & Earth Sciences (AREA)
  • Length Measuring Devices With Unspecified Measuring Means (AREA)

Abstract

The invention discloses a size detection method of a turbine blade disc, which comprises the following steps: establishing an iterative coordinate system; according to the structure of the turbine blade disc, measuring the numerical value of a to-be-measured point by using a software program, and detecting the channel size; determining the length of the throat by adopting a software circulation statement program; measuring the actual throat area of the turbine blade disc to be measured by adopting a large-circulation program of software; calculating the average value of the channel and the throat; printing the measured actual area of the throat, the measured channel and the measured average value of the throat, and storing the data; according to the invention, the measuring needle of the three-coordinate measuring instrument is utilized to automatically rotate the angle according to the number of the blades of the turbine blade disc, a turntable is not needed, the cost and precision errors of the turntable are reduced, meanwhile, the angle of the measuring needle can be automatically adjusted according to the number of the blades, and the detection efficiency is high and the detection cost is low by using a circulation statement, so that the method is not limited by the self-size requirement of the turbine disc.

Description

Size detection method for turbine blade disc
Technical Field
The invention relates to the technical field of turbine blade size detection, in particular to a size detection method of a turbine blade disc.
Background
The turbine blade disc of the combustion engine is a relatively common product, the application field is very wide, the main function of the turbine blade disc is to control wind speed guiding, the structure of the turbine blade disc is very complex, each blade needs to be detected, the profile, throat area, channel and the like of the blade are all critical dimensions, the number of the blades needing to be detected is large, the detection parameters are large, the angle needs to be continuously changed when each blade is detected, the detection difficulty is large, the detection time is long, errors exist when the angle is changed, the detection precision is reduced, a turntable is needed to be used for rotating the turbine blade disc, the additional cost is increased, and a set of special method for detecting the turbine blade disc is researched for the detection difficulty, so that the method is convenient and quick, and the cost for purchasing the turntable can be reduced.
Disclosure of Invention
The invention mainly aims to provide a size detection method of a turbine blade disc, which utilizes a measuring pin of a three-coordinate measuring instrument to automatically rotate an angle according to the number of blades of the turbine blade disc, a turntable is not needed, cost and precision errors of the turntable are reduced, meanwhile, the angle of the measuring pin can be automatically adjusted according to the number of the blades, a circulation statement is utilized, the detection efficiency is high, the detection cost is low, the limitation of the size requirement of the turbine disc is avoided, and the problem in the background technology can be effectively solved.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: a method of detecting the size of a turbine disk comprising the steps of:
step one, establishing an iterative coordinate system: importing a three-dimensional graph of a turbine blade disc to be tested into a three-dimensional coordinate measuring instrument, and establishing an iterative coordinate system by adopting a 321 iteration principle according to the three-dimensional graph;
step two, channel detection: according to the structure of the turbine blade disc, a plurality of points to be measured are selected on an inner ring and an outer ring which correspond to the blades, the points to be measured are constructed into an outer circle and an inner circle, the numerical values of the points to be measured are measured by a software program, the diameter D of the outer circle and the diameter D of the inner circle are obtained by measurement, and half of the diameter difference Deltad of each point to be measured of the two circles is the channel size;
step three, detecting the length of the throat: measuring the distance between the middle value of the blade channel of the turbine blade disc and the center of the circle of the inner ring of the turbine blade disc by using a software program, automatically rounding the rotation angle of the probe on the three-coordinate measuring instrument by using a software circulation statement program, and then measuring the length of the throat by using the software circulation statement program;
step four, calculating the actual area of the throat of the turbine blade: according to the measured channel size and throat length size, using axiom of the product of length and width of the area, and adopting a large-circulation program of software to measure the actual throat area of the turbine blade disk to be measured;
step five, calculating the average value of the channel and the throat: the channel size between each to-be-measured point measured in the step two is summed and divided by the number of the selected to-be-measured points to obtain the average width of the channel through a software program, and the throat length between every two adjacent blades measured in the step three is summed and divided by the number of all the throats to obtain the average length of the throats through the software program;
step six, printing and storing: and (3) printing the actual area of the throat, the average value of the channel and the throat measured in the step four and the step five, and storing data.
Preferably, the establishing an iteration coordinate system in the first step includes a coarse-building iteration coordinate system and a fine-building iteration coordinate system.
Preferably, the step of the rough construction iteration coordinate system is to select three blades with 120-degree intervals in the imported three-dimensional graph, find three vector points in the Z direction on the exhaust edge of each blade, measure a circle on the inner ring of the turbine blade, find two points on the exhaust edges of two symmetrical blades, the vector direction is the X direction, select three points as a plane according to 321 iteration principles, the point on the two exhaust edges is the line, the circle center is used as a point to determine the position, and the rough construction iteration coordinate system.
Preferably, the step of the fine construction iteration coordinate system is to select four equally divided blades in a three-dimensional graph on the basis of a coarse construction iteration coordinate system, select the highest point of each blade in the Z-axis direction, then measure a circle on an inner ring of a turbine blade disc, find out two high points in the X-direction on the exhaust edges of two symmetrical blades, select four points as a plane according to 321 iteration principles, select the points on the two exhaust edges as a line, and the circle center as a point to determine the position, and finely construct the iteration coordinate system.
Preferably, in the second step, the points to be measured on the outer circle and the inner circle are sequentially measured by using a circulation statement program of the software program, and half of the difference between the corresponding points to be measured on the outer circle and the inner circle is the channel size.
Preferably, the width dimension of the single channel in the second step is measured by a software program to measure the distance between two points located on the same axis.
Preferably, the number of the to-be-measured points in the second step is identical to the number of the blades in the turbine blade disc, and corresponds to two end parts of the blades.
Preferably, in the third step, the distance between the middle value of the blade channel of the turbine blade disc and the center of the circle of the inner ring of the turbine blade disc is (D+d)/4.
Compared with the prior art, the invention has the beneficial effects that: according to the invention, the measuring needle of the three-coordinate measuring instrument is utilized to automatically rotate the angle according to the number of the blades of the turbine blade disc, a turntable is not needed, the cost and precision errors of the turntable are reduced, meanwhile, the angle of the measuring needle can be automatically adjusted according to the number of the blades, and the detection efficiency is high and the detection cost is low by using a circulation statement, so that the method is not limited by the self-size requirement of the turbine disc.
Drawings
Fig. 1 is a schematic view of a turbine disc structure according to embodiment 2 of the present invention.
In the figure: 1. a turbine blade disc; 2. an outer ring; 3. an inner ring; 4. a blade; 5. a throat.
Description of the embodiments
The invention is further described in connection with the following detailed description, in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the invention easy to understand.
Examples
A method of detecting the size of a turbine disk comprising the steps of:
step one, establishing an iterative coordinate system: importing a three-dimensional graph of a turbine blade disc to be tested into a three-dimensional coordinate measuring instrument, and establishing an iterative coordinate system by adopting a 321 iteration principle according to the three-dimensional graph;
step two, channel detection: according to the structure of the turbine blade disc, a plurality of points to be measured are selected on an inner ring and an outer ring which correspond to the blades, the points to be measured are constructed into an outer circle and an inner circle, the numerical values of the points to be measured are measured by a software program, the diameter D of the outer circle and the diameter D of the inner circle are obtained by measurement, and half of the diameter difference Deltad of each point to be measured of the two circles is the channel size;
step three, detecting the length of the throat: measuring the distance between the middle value of the blade channel of the turbine blade disc and the center of the circle of the inner ring of the turbine blade disc by using a software program, automatically rounding the rotation angle of the probe on the three-coordinate measuring instrument by using a software circulation statement program, and then measuring the length of the throat by using the software circulation statement program;
step four, calculating the actual area of the throat of the turbine blade: according to the measured channel size and throat length size, using axiom of the product of length and width of the area, and adopting a large-circulation program of software to measure the actual throat area of the turbine blade disk to be measured;
step five, calculating the average value of the channel and the throat: the channel size between each to-be-measured point measured in the step two is summed and divided by the number of the selected to-be-measured points to obtain the average width of the channel through a software program, and the throat length between every two adjacent blades measured in the step three is summed and divided by the number of all the throats to obtain the average length of the throats through the software program;
step six, printing and storing: and (3) printing the actual area of the throat, the average value of the channel and the throat measured in the step four and the step five, and storing data.
Preferably, the establishing an iteration coordinate system in the first step includes a coarse-building iteration coordinate system and a fine-building iteration coordinate system.
Preferably, the step of the rough construction iteration coordinate system is to select three blades with 120-degree intervals in the imported three-dimensional graph, find three vector points in the Z direction on the exhaust edge of each blade, measure a circle on the inner ring of the turbine blade, find two points on the exhaust edges of two symmetrical blades, the vector direction is the X direction, select three points as a plane according to 321 iteration principles, the point on the two exhaust edges is the line, the circle center is used as a point to determine the position, and the rough construction iteration coordinate system.
Preferably, the step of the fine construction iteration coordinate system is to select four equally divided blades in a three-dimensional graph on the basis of a coarse construction iteration coordinate system, select the highest point of each blade in the Z-axis direction, then measure a circle on an inner ring of a turbine blade disc, find out two high points in the X-direction on the exhaust edges of two symmetrical blades, select four points as a plane according to 321 iteration principles, select the points on the two exhaust edges as a line, and the circle center as a point to determine the position, and finely construct the iteration coordinate system.
Preferably, in the second step, the points to be measured on the outer circle and the inner circle are sequentially measured by using a circulation statement program of the software program, and half of the difference between the corresponding points to be measured on the outer circle and the inner circle is the channel size.
Preferably, the width dimension of the single channel in the second step is measured by a software program to measure the distance between two points located on the same axis.
Preferably, the number of the to-be-measured points in the second step is identical to the number of the blades in the turbine blade disc, and corresponds to two end parts of the blades.
Preferably, in the third step, the distance between the middle value of the blade channel of the turbine blade disc and the center of the circle of the inner ring of the turbine blade disc is (D+d)/4.
Examples
As shown in FIG. 1, the turbine blade on the gas turbine with the diameter of 450mm is composed of an inner ring, an outer ring and 36 blades, wherein the 36 blades all need to be detected, and the throat area and the blade profile are mainly checked.
A method of detecting the size of a turbine disk comprising the steps of:
step one, establishing an iterative coordinate system: before measurement, a three-dimensional graph of a turbine blade disc to be measured is led into a three-dimensional measuring instrument, an iteration coordinate system is established according to the three-dimensional graph by adopting a 321 iteration principle, and an appropriate three-dimensional coordinate system is selected.
The coordinate system may be adjusted by drawing software or from PC-DIMS at the time of selection.
Establishing an iteration coordinate system comprises a coarse construction iteration coordinate system and a fine construction iteration coordinate system, wherein:
the rough construction iteration coordinate system comprises the steps of selecting three blades with 120-degree intervals in an imported three-dimensional graph, finding three vector points in the Z direction on the exhaust edge of each blade, wherein the selected vector points are preferably the middle points of channels of single blades, measuring a circle on an inner ring of a turbine blade, finding two points on the exhaust edges of two symmetrical blades, finding the vector direction to be the X direction, selecting the three points as a plane according to the 321 iteration principle, selecting the point on the two exhaust edges as the most line, determining the position by taking the center of a circle as one point, and rough construction iteration coordinate system.
The method comprises the steps of adopting a rough construction iteration coordinate system based on the rough construction iteration coordinate system, selecting four equally divided blades in a three-dimensional graph, selecting the highest point of each blade in the Z-axis direction, wherein the highest point is required to have a specific numerical value in a three-dimensional drawing from a point to a circle center, measuring a circle on an inner ring of a turbine blade disc, finding out high points in two X directions on exhaust edges of two symmetrical blades, wherein the high points are also the midpoint position of a blade channel, selecting four points as a plane according to a 321 iteration principle, selecting the points on the two exhaust edges as a line, and determining the position by taking the circle center as a point.
Step two, channel detection: according to the structure of the turbine blade disc, the turbine disc in the embodiment is different from a common circular ring, a blade is arranged in the middle of the turbine disc, a probe cannot directly measure a circle when measuring the size of a channel, 36 points to be measured are selected on an inner circular ring and an outer circular ring corresponding to the blade to form an outer circle and an inner circle, the numerical value of the points to be measured is measured by a software program, the outer circle diameter D and the inner circle diameter D are obtained by measuring, one half of the difference delta D between the two circles is the average size of the channel, an array can be used or a circular sentence can be used when measuring the measuring points, in the embodiment, in order to save the space of the program, the size of a single channel can be regarded as the distance between two points on one axis, and therefore, the size measurement between the single channels is the distance between the two points measured by adopting the software program;
step three, detecting the length of the throat: the turbine blade disc has errors during casting, and the distance between the intermediate value of the blade channel and the center of the inner ring of the turbine blade disc has certain errors, so that the distance between the intermediate value of the blade channel and the center of the inner ring needs to be calculated, and the inner ring and the outer ring are constructed in channel detection, so that a formula program is compiled for the distance between the intermediate value of the blade channel and the center of the inner ring of the turbine blade disc, and the specific formula program is as follows: assignment/v1=inside circle diameter
Assignment/v2=excircle.diam
Assignment v6= (v1+v2)/4
The calculated V6 value is the distance between the middle value of the blade channel and the center of the circle of the inner ring of the turbine blade disc.
After the preliminary preparation, the throat length is measured, whereas the turbine disk in this example consists of 36 blades, the rotation angle is also very large, in this example the probe is not turned 7.5 °, so the probe rotation is automatically rounded by the cyclic statement, the calculation procedure is:
c1 Note/input, no, full screen=no,
please input the number to be measured
Assignment/num=c1.input
Assignment/count=1
assignment/v1=360/NUM
WHILE/COUNT<=NUM
Assignment/v2=v1 (COUNT-1)
Assignment/v3=int (V2/7.5)
Assignment/v4= (V2/7.5) -INT (V2/7.5)
IF/V4>0.5
Assignment/v3=v3+1
END_IF/
Assignment/angle=90-a
A4 =coordinate system/start, callback: A3, list=yes (A3 is the refined iterative coordinate system)
Establishing a coordinate system/rotational offset, V2, positive with respect to Z
Build coordinate System/rotation bias, -ANGLE, about X positive
Coordinate system/termination
In the calculation procedure, the coordinate system rotates continuously along with the increase of the number of the blades, the Z axis rotates 90-a around the X axis on the basis of A3, and the X axis rotates V2 around the Z axis, so that the highest point E perpendicular to the exhaust edge under the angle a is found.
The throat length is measured by adopting a cyclic statement program, wherein the cyclic statement program is as follows:
assignment/v5=v3×7.5
IF/V5>180
Assignment/v5=v5-360
END_IF/
Assignment/tipname= "T1A (90-a)" + "B" +v5
tip/TIPNAME, support direction ijk=0, 0, 1, angle=oo (angle found on three-dimensional map)
Assignment/xx=v6
Assignment/yy=oo (Y value found on three-dimensional map)
Assignment/zz=oo (Z value found on three-dimensional map)
Assignment/ii=0
Assignment/jj=0
Assignment/kk=1
Point E = feature/touch/high point/default, rectangular coordinates
Theoretical values/< XX, YY, ZZ >, < II, JJ, KK >
Actual values/< 151.8954, -15.8209, -17.7852>, <0.1481146,0.2318286,0.9614144>
Target/< XX, YY, ZZ >, < II, JJ, KK >
Increment=0.1, tolerance=0.05, square, width=0, length=3
Center= < XX, YY, ZZ-
Display characteristic parameter = no
Display related parameter=no (this point is the blade channel midpoint)
assignment/VV = point e.xyz
Whether the document is a document or not,
VV
assignment/ii=0
Assignment/jj=1
Assignment/kk=0
Point TE = feature/touch/vector point/default, rectangular coordinates
Theoretical value/< XX, VV.Y, VV.Z-value of maximum point of exhaust side angle a (the drawing will generally be) >, < II, JJ, KK >
Actual values/< 151.8808, -15.1218, -18.4996>, <0.0628868,0.9404493, -0.3340664>
Target value/< XX, VV.Y, VV.Z-value of maximum point of exhaust side angle a (the drawing will generally be) > < II, JJ, KK >
Catch = no
Display characteristic parameter = no
Display related parameter = no (throat value first point)
assignment/VV = point te.xyz
Whether the document is a document or not,
VV
assignment/ii=0
Assignment/jj= -1
Assignment/kk=0
Point CV = feature/touch/vector point/default, rectangular coordinates
Theoretical values/< XX, VV.Y+throat length, VV.Z >, < II, JJ, KK >
Actual values/< 152.4707, -7.2238, -20.917>, <0.031403, -0.9791629,0.2006338>
Target/< XX, VV.Y+throat length, VV.Z >, < II, JJ, KK >
Catch = no
Display characteristic parameter = no
Display related parameter = no (throat value second point)
Assignment/ii=0
Assignment/jj=1
Assignment/kk=0
Work plane/Y positive
Point LE = feature/touch/high point/default, rectangular coordinates
Theoretical values/< XX, VV.Y, VV.Z-OO (the value of the highest point from TE point found on the three-dimensional map) > < II, JJ, KK >
Actual values/< 147.6491, -14.8854, -52.015>, <0.1044626,0.9944286, -0.0141191>
Target value/< XX, VV.Y, VV.Z-OO (the value of the highest point of the air inlet edge, the distance TE point is found on the three-dimensional map) > < II, JJ, KK >
Increment=0.1, tolerance=0.05, square, width=0, length=3
Center= < XX, vv.y, vv.z-OO (the highest point of the intake side is found on the three-dimensional map, the value from TE point) >
Display characteristic parameter = no
Display related parameter = no (throat angle second point)
A5 =coordinate system/start, callback: A3, list=yes
Establishing a coordinate system/rotational offset, V2, positive with respect to Z
Coordinate system/termination
Work plane/X positive
Straight line 1 = feature/straight line, rectangular coordinates, non-bounding, no
Theoretical values/< 153.1051,1.0835, -0.1496>, <0, -0.738601, -0.6741429>
Actual values/< 151.8808, -23.8774, -0.881>, < -0.1252642, -0.7398321, -0.6610275>
Construction/straight line, best fit, 2D, point TE, point LE,
local outer layer_remove/off, 3
Filter/off, wavelength=0
DIM angle 1=2d angle from straight line 1 to Y axis, $
(evaluation angle)
Work plane/Z positive
assignment/VV = point cv.xyz
Whether the document is a document or not,
VV
assignment/count=count+1
END_WHILE/
Callback/coordinate System, in, A3
Assignment/c=1
Assignment/v11=0
WHILE/C<=NUM
Measuring the actual area of the throat of the turbine blade disc to be measured by adopting a large circulation program, wherein the actual area of a single throat is the product of the length of the throat and half of the width of the channel, and the planar structure of the throat is trapezoid;
the cyclic procedure is:
DIM distance e=3D from point TE [ C ] to point CV [ C ], shortest=on, no radius unit=millimeter, $
Graph = off text = off magnification = 10.00 output = both
AX NOMINAL MEAS DEV +TOL -TOL
M OO OO OO OO OO
DIM distance l=3D from point IR [ C ] to point OR [ C ], shortest=on, no radius unit=millimeter, $
Graph = off text = off magnification = 10.00 output = both
AX NOMINAL MEAS DEV +TOL -TOL
M OO OO OO OO OO
Assignment/v11= (distance L [ C ]. MEAS distance E [ C ]. MEAS) +v11
Assignment/c=c+1
END_WHILE/
IF/NUM==36
The average length of the throat is calculated:
assignment/ea=sum (ARRAY (distance E1. MEAS, distance E2. MEAS, distance E3. MEAS, distance E4. MEAS, distance E5. MEAS, distance E6. MEAS, distance E7. MEAS, distance E8. MEAS, distance E9. MEAS, distance E10. MEAS, distance E11. MEAS, distance E12. MEAS, distance E13. MEAS, distance E14. MEAS))
assignment/EA 1 = SUM (ARRAY (distance E15. MEAS, distance E16. MEAS, distance E17. MEAS, distance E18. MEAS, distance E19. MEAS, distance E20. MEAS, distance E21. MEAS, distance E22. MEAS, distance E23. MEAS, distance E24. MEAS, distance E25. MEAS, distance E26. MEAS, distance E27. MEAS, distance E28. MEAS))
assignment/EA 2 = SUM (ARRAY (distance E29. MEAS, distance E30. MEAS, distance E31. MEAS, distance E32. MEAS, distance E33. MEAS, distance E34. MEAS, distance E35. MEAS, distance E36. MEAS))
Assignment/v66= (ea+ea 1+ea 2)/36
Calculating the average width of the channels:
assignment of la=sum (ARRAY (distance L1. MEAS, distance L2. MEAS, distance L3. MEAS, distance L4. MEAS, distance L5. MEAS, distance L6. MEAS, distance L7. MEAS, distance L8. MEAS, distance L9. MEAS, distance L10. MEAS, distance L11. MEAS, distance L12. MEAS, distance L13. MEAS, distance L14. MEAS))
assignment/LA 1 = SUM (ARRAY (distance L15. MEAS, distance L16. MEAS, distance L17. MEAS, distance L18. MEAS, distance L19. MEAS, distance L20. MEAS, distance L21. MEAS, distance L22. MEAS, distance L23. MEAS, distance L24. MEAS, distance L25. MEAS, distance L26. MEAS, distance L27. MEAS, distance L28. MEAS))
assignment/LA 2 = SUM (ARRAY (distance L29. MEAS, distance L30. MEAS, distance L31. MEAS, distance L32. MEAS, distance L33. MEAS, distance L34. MEAS, distance L35. MEAS, distance L36. MEAS))
Assignment/v77= (la+la1+la2)/36
The editor program prints the throat area, average throat length, and average channel width of the turbine blade, wherein:
the throat area printing program of the turbine blade is as follows:
f1 =general/point, subordinate, rectangular coordinates, $
Nominal value/XYZ, < AA (area required for drawing), 0>, $
Measurement value/XYZ, < V11,194.206,96.3514>, $
Nominal value/IJK, <0, -1>, $
Measurement value/IJK, <0, -1>
The annotation/report is made,
* Total area
DIM position 2=position F1 standard deviation of point=0.0000 unit=millimeter, $
Graph = off text = off magnification = 10.00 output = half angle of both = no
AX NOMINAL MEAS DEV +TOL -TOL
X AA OO OO OO OO
End size position 2
Assignment/bb=drawing requirement value
The average throat printing procedure for the turbine blade is:
f1 =general/point, subordinate, rectangular coordinates, $
Nominal value/XYZ, < BB, 0>, $
Measurement value/XYZ, < V66, -167.0342,110.6852>, $
Nominal value/IJK, <0, -1>, $
Measurement value/IJK, <0, -1>
The annotation/report is made,
* Average throat E
DIM position 2=position F1 standard deviation of point=0.0000 unit=millimeter, $
Graph = off text = off magnification = 10.00 output = half angle of both = no
AX NOMINAL MEAS DEV +TOL -TOL
X BB OO OO OO OO
End size position 2
Assignment/dd=drawing requirement value
The average channel printing program for the turbine blade is:
f1 =general/point, subordinate, rectangular coordinates, $
Nominal value/XYZ, < DD, 0>, $
Measurement value/XYZ, < V77, -167.3431,110.6841>, $
Nominal value/IJK, <0, -1>, $
Measurement value/IJK, <0, -1>
The annotation/report is made,
* Average channel
DIM position 2=position F1 standard deviation of point=0.0000 unit=millimeter, $
Graph = off text = off magnification = 10.00 output = half angle of both = no
AX NOMINAL MEAS DEV +TOL -TOL
X DD OO OO OO OO
End size position 2
END_IF/
After printing is completed, the measured data is stored.
The method adopts the program to automatically save, and specifically comprises the following steps:
assignment/v1= "path of storage disk to select one folder" +c2.input (C2 is part number, assignment at program start)
Print/report, execution mode = terminate, $
To file = on, overlay = v1.pdf, $
To printer=off $
To dmis_report=off, file_option=index, file name=, $
Report_theory = none, report_feature_and_size = no, $
Previous run = delete instance
The method is simple and effective, the measuring needle of the three-coordinate measuring instrument is utilized to automatically rotate the angle according to the number of the blades of the turbine blade disc, the turntable is not needed for detection, the extra cost is reduced, the cost is saved, the cyclic statement program is adopted for operation, no precision error exists, the detection of the turbine blade disc is not limited in size, and the method is simple and convenient.
The detection method reduces cost and precision errors of the turntable, can automatically adjust the angle of the measuring needle according to the number of the blades, has high detection efficiency by using a circulation statement, has low detection cost, and is not limited by the self-size requirement of the turbine disc.
While certain exemplary embodiments of the present invention have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that modifications may be made to the described embodiments in various different ways without departing from the spirit and scope of the invention. Accordingly, the drawings and description are to be regarded as illustrative in nature and not as restrictive of the scope of the invention, which is defined by the appended claims.

Claims (8)

1. A method for detecting the size of a turbine impeller, which is characterized by comprising the following steps: the method comprises the following steps:
step one, establishing an iterative coordinate system: importing a three-dimensional graph of a turbine blade disc to be tested into a three-dimensional coordinate measuring instrument, and establishing an iterative coordinate system by adopting a 321 iteration principle according to the three-dimensional graph;
step two, channel detection: according to the structure of the turbine blade disc, a plurality of points to be measured are selected on an inner ring and an outer ring which correspond to the blades, the points to be measured are constructed into an outer circle and an inner circle, the numerical values of the points to be measured are measured by a software program, the diameter D of the outer circle and the diameter D of the inner circle are obtained by measurement, and half of the diameter difference Deltad of each point to be measured of the two circles is the channel size;
step three, detecting the length of the throat: measuring the distance between the middle value of the blade channel of the turbine blade disc and the center of the circle of the inner ring of the turbine blade disc by using a software program, automatically rounding the rotation angle of the probe on the three-coordinate measuring instrument by using a software circulation statement program, and then measuring the length of the throat by using the software circulation statement program;
step four, calculating the actual area of the throat of the turbine blade: according to the measured channel size and throat length size, using axiom of the product of length and width of the area, and adopting a large-circulation program of software to measure the actual throat area of the turbine blade disk to be measured;
step five, calculating the average value of the channel and the throat: the channel size between each to-be-measured point measured in the step two is summed and divided by the number of the selected to-be-measured points to obtain the average width of the channel through a software program, and the throat length between every two adjacent blades measured in the step three is summed and divided by the number of all the throats to obtain the average length of the throats through the software program;
step six, printing and storing: and (3) printing the actual area of the throat, the average value of the channel and the throat measured in the step four and the step five, and storing data.
2. The method for detecting the size of a turbine disk according to claim 1, wherein: in the first step, the establishing of the iterative coordinate system includes coarse-building iterative coordinate system and fine-building iterative coordinate system.
3. A method of detecting the size of a turbine disk according to claim 2, characterized in that: the rough construction iteration coordinate system comprises the steps of selecting three blades with 120-degree intervals in an imported three-dimensional graph, finding three vector points in the Z direction on the exhaust edge of each blade, measuring a circle on the inner ring of the turbine blade, finding two points on the exhaust edges of two symmetrical blades, wherein the vector direction is the X direction, selecting the three points as a plane according to the 321 iteration principle, determining the position of the circle center as a point on the two exhaust edges, and rough construction iteration coordinate system.
4. A method of detecting the size of a turbine disk according to claim 2, characterized in that: the fine construction iteration coordinate system comprises the steps of selecting four equally-divided blades in a three-dimensional graph on the basis of a coarse construction iteration coordinate system, selecting the highest point of each blade in the Z-axis direction, measuring a circle on an inner ring of a turbine blade disc, finding out two high points in the X-direction on exhaust edges of two symmetrical blades, selecting four points as a plane according to a 321 iteration principle, selecting points on the two exhaust edges as a line, and determining the position by taking the circle center as a point.
5. The method for detecting the size of a turbine disk according to claim 1, wherein: and in the second step, the points to be measured on the outer circle and the inner circle are sequentially measured by using a circulation statement program of the software program, and half of the difference value between the corresponding points to be measured on the outer circle and the inner circle is the channel size.
6. The method for detecting the size of a turbine disk according to claim 1, wherein: the width dimension of the single channel in the second step is measured by a software program to measure the distance between two points on the same axis.
7. The method for detecting the size of a turbine disk according to claim 1, wherein: and in the second step, the number of the to-be-measured points is consistent with the number of the blades in the turbine blade disc, and the to-be-measured points correspond to the two end parts of the blades.
8. The method for detecting the size of a turbine disk according to claim 1, wherein: and in the third step, the distance between the middle value of the blade channel of the turbine blade disc and the center of the circle of the inner ring of the turbine blade disc is (D+d)/4.
CN202111311621.8A 2021-11-08 2021-11-08 Size detection method for turbine blade disc Active CN114252035B (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2389484A1 (en) * 2002-06-06 2003-12-06 Pratt & Whitney Canada Inc. Optical measuremnet of vane ring throat area
US8196305B1 (en) * 2011-01-25 2012-06-12 General Electric Company Turbine blade measuring device
CN103335586A (en) * 2013-06-08 2013-10-02 沈阳黎明航空发动机(集团)有限责任公司 Design method of guiding N united blade air discharge area simulation assembly detection device
CN104990531A (en) * 2015-07-06 2015-10-21 中国航空工业集团公司沈阳发动机设计研究所 Method for measuring exhaust area of turbine nozzle
CN113607119A (en) * 2021-07-26 2021-11-05 中国船舶重工集团公司第七0三研究所 Method for measuring throat area of marine gas turbine blade based on characteristic dimension
CN113513369B (en) * 2021-07-26 2023-01-24 中国船舶重工集团公司第七0三研究所 Method for adjusting throat area of turbine blade of marine gas turbine

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