CN116448026A - Standard component and method for calibrating high-pressure turbine working blade gas film hole measuring equipment - Google Patents
Standard component and method for calibrating high-pressure turbine working blade gas film hole measuring equipment Download PDFInfo
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- CN116448026A CN116448026A CN202310550808.6A CN202310550808A CN116448026A CN 116448026 A CN116448026 A CN 116448026A CN 202310550808 A CN202310550808 A CN 202310550808A CN 116448026 A CN116448026 A CN 116448026A
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 239000000758 substrate Substances 0.000 claims abstract description 87
- 238000005259 measurement Methods 0.000 claims abstract description 26
- 150000001875 compounds Chemical class 0.000 claims description 8
- 238000012937 correction Methods 0.000 claims description 7
- 238000013461 design Methods 0.000 claims description 4
- 239000013307 optical fiber Substances 0.000 claims description 4
- 238000010276 construction Methods 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims description 3
- 239000000523 sample Substances 0.000 claims description 3
- 239000002131 composite material Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 5
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
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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
-
- 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
- G01B21/04—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 by measuring coordinates of points
- G01B21/042—Calibration or calibration artifacts
-
- 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
- G01B21/20—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring contours or curvatures, e.g. determining profile
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The application belongs to the technical field of aeroengine high-pressure turbine working vane air film hole measurement, and in particular relates to a standard component and a method for calibrating high-pressure turbine working vane air film hole measurement equipment, wherein the standard component comprises: the first base plate is provided with a standard leaf basin curved surface, and the standard leaf basin curved surface is provided with 1 st to 5 th rows of standard air film holes; the second substrate is arranged perpendicular to the first substrate, and is provided with a standard blade back curved surface, and the standard blade back curved surface is provided with 6 th-10 th rows of standard air film holes; the third substrate is vertically arranged with the first substrate and the second substrate, and is provided with a standard front edge curved surface, and the standard front curved surface is provided with 11 th-15 th row standard air film holes; each row of standard air film holes is provided with 6 standard air film holes which are vertical to the plane of the substrate; the transverse spacing of the standard gas film holes in the 1 st row to the 5 th row, the standard gas film holes in the 6 th row to the 10 th row and the standard gas film holes in the 11 th row to the 15 th row are 4.5mm, and the longitudinal spacing is 8mm.
Description
Technical Field
The application belongs to the technical field of measurement of air film holes of high-pressure turbine working blades of aeroengines, and particularly relates to a standard component and a method for calibrating air film holes of high-pressure turbine working blades.
Background
The air film holes on the high-pressure turbine working blades of the aeroengine have very important significance for cooling the high-pressure turbine working blades, the distribution of the air film holes on the high-pressure turbine working blades is shown in a figure 1, the number of the air film holes on the high-pressure turbine working blades is large, the diameter is small, the space distribution is complex, the air film holes on the high-pressure turbine working blades are precisely measured, and the air film holes on the high-pressure turbine working blades can be objectively evaluated.
At present, when measuring the air film hole on the high-pressure turbine working blade of the aeroengine, repeated multiple measurement is carried out by using measuring equipment, but a calibration means for measuring the measuring accuracy of the measuring equipment is lacked, the accuracy of measuring the air film hole on the high-pressure turbine working blade cannot be ensured, and the processing quality of the air film hole on the high-pressure turbine working blade cannot be accurately evaluated.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
The purpose of the application is to provide a standard part and a method for calibrating high-pressure turbine working blade air film hole measuring equipment, which overcome or alleviate the technical defects of at least one aspect in the prior art.
The technical scheme of the application is as follows:
in one aspect, a calibration standard for a high-pressure turbine rotor blade gas film hole measurement device is provided, including:
the first base plate is provided with a standard leaf basin curved surface, and the standard leaf basin curved surface is provided with 1 st to 5 th rows of standard air film holes;
the second substrate is arranged perpendicular to the first substrate, and is provided with a standard blade back curved surface, and the standard blade back curved surface is provided with 6 th-10 th rows of standard air film holes;
the third substrate is vertically arranged with the first substrate and the second substrate, and is provided with a standard front edge curved surface, and the standard front curved surface is provided with 11 th-15 th row standard air film holes;
each row of standard air film holes is provided with 6 standard air film holes which are vertical to the plane of the substrate;
the diameters of the 1 st, 3 rd, 5 th, 6 th, 8 th, 10 th, 11 th, 13 th and 15 th standard air film holes are all 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm;
the diameters of the standard air film holes in the rows 2, 4, 7, 9, 12 and 14 are all 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm;
the transverse spacing of the standard gas film holes in the 1 st row to the 5 th row, the standard gas film holes in the 6 th row to the 10 th row and the standard gas film holes in the 11 th row to the 15 th row are 4.5mm, and the longitudinal spacing is 8mm.
Optionally, in the standard component for calibrating the high-pressure turbine rotor blade air film hole measuring equipment, the planeness of the first substrate, the second substrate and the third substrate is 0.01mm, and the verticality is 0.01mm;
the position degree of each row of standard air film holes relative to the substrate is 0.01mm.
Optionally, in the calibration standard component for the high-pressure turbine rotor blade gas film hole measurement device, the method further includes:
one end of the straight rod connecting rod is in threaded connection with the corner parts of the first base plate, the second base plate and the third base plate, and the other end of the straight rod connecting rod is connected with the turntable of the measuring equipment.
Optionally, in the calibration standard component for the high-pressure turbine rotor blade gas film hole measurement device, the method further includes:
one end of the first connecting rod is in threaded connection with corner parts of the first base plate, the second base plate and the third base plate;
and one end of the second connecting rod is connected with the other end of the first connecting rod through a single-double-lug structure by utilizing a screw, and the other end of the second connecting rod is connected with the turntable of the measuring equipment.
On the other hand, the calibration method for the standard component for calibrating the high-pressure turbine rotor blade air film hole measuring equipment comprises the following steps:
the method comprises the steps of calibration preparation, namely placing a standard component for calibrating high-pressure turbine working blade air film hole measuring equipment on a workbench of a compound coordinate measuring machine, and enabling a third substrate to be horizontally upwards;
a reference surface measuring step of measuring the planes of the first substrate, the second substrate and the third substrate by adopting a probe sensor of a composite coordinate measuring machine;
a measurement coordinate system construction step, namely, taking the normal direction of the second substrate plane as an X axis, the normal direction of the third substrate plane as a Y axis, taking the normal direction of the first substrate plane as a Z axis, and taking the intersection point of the first substrate, the second substrate and the third substrate plane as an origin to construct a measurement coordinate system;
a coordinate fitting step, namely introducing a standard part three-dimensional model for calibrating the high-pressure turbine working blade air film hole measuring equipment into a composite coordinate measuring machine, and fitting a model coordinate system and a measuring coordinate system;
a digital-analog guiding optical fiber measuring step, namely calling a composite coordinate measuring machine, programming a measuring program according to digital-analog guiding, completing measurement of each row of standard air film holes on a third substrate, adjusting the first substrate to be horizontally upwards to complete measurement of each row of standard air film holes on the first substrate, adjusting the second substrate to be horizontally upwards to complete measurement of each row of standard air film holes on the second substrate;
and a calibration and correction step, namely comparing measured values of the diameter, cylindricity and position degree of each row of standard air film holes with design values, and calculating correction errors.
Drawings
FIG. 1 is a schematic diagram of the distribution of gas film holes of a working blade of a high-pressure turbine of an existing aeroengine;
FIG. 2 is a schematic diagram of a calibration standard for high pressure turbine rotor blade gas film hole measurement equipment provided in an embodiment of the present application;
fig. 3 is a schematic coordinate diagram of a calibration standard component for a high-pressure turbine working vane gas film hole measuring device according to an embodiment of the present application;
FIG. 4 is a schematic view of a straight rod connecting rod of a standard piece for calibrating a high-pressure turbine working blade gas film hole measuring device provided by the embodiment of the application;
fig. 5 is a schematic diagram of a calibration standard component with a first connecting rod and a second connecting rod for a high-pressure turbine working vane gas film hole measuring device provided by an embodiment of the application;
FIG. 6 is a schematic diagram of a calibration method of a calibration standard for high pressure turbine rotor blade gas film hole measurement equipment provided in an embodiment of the present application;
FIG. 7 is a flowchart of a method for calibrating a standard component for calibrating high-pressure turbine rotor blade gas film hole measurement equipment provided in an embodiment of the present application;
wherein:
1-a first substrate; 2-a second substrate; 3-a third substrate; 4-a straight rod connecting rod; 5-a first link; 6-a second link; 7-compound coordinate measuring machine.
For better illustration of the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present application.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below in conjunction with fig. 1-7.
The utility model provides a high-pressure turbine rotor blade air film hole measuring equipment calibration standard component, simple structure, overall arrangement are compact, can realize the simulation of different diameters, different space angle and different spatial position's air film hole, calibrate through high accuracy measuring equipment, can be used for calibrating air film hole measuring equipment after the calibration, can satisfy the calibration of air film hole measuring equipment under the multiple condition.
The structure of the standard component for calibrating the high-pressure turbine working vane air film hole measuring equipment is shown in fig. 2, the main body consists of three mutually perpendicular thin-wall first base plates 1, second base plates 2 and third base plates 3, and standard vane basin curved surfaces, standard vane back curved surfaces and standard front edge curved surfaces are respectively formed, so that the molded surfaces of the high-pressure turbine working vane air film holes of the aero-engine are simulated, and the vane basin, the vane back and the front edge curved surfaces are formed.
The standard blade basin curved surface, the standard blade back curved surface and the standard front edge curved surface are provided with 15 rows of standard air film holes, wherein the 1 st to 5 th rows of standard air film holes are positioned on the standard blade basin curved surface, the 6 th to 10 th rows of standard air film holes are positioned on the standard front edge curved surface, each row of standard air film holes are provided with 6 holes, the total number of the standard air film holes is 90, all the standard air film holes are through holes, and all the standard air film holes are perpendicular to the plane of the substrate.
The diameters of the 1 st, 3 rd, 5 th, 6 th, 8 th, 10 th, 11 th, 13 th and 15 th standard air film holes are all 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the standard air film holes in the rows 2, 4, 7, 9, 12 and 14 are all 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the transverse spacing of the standard gas film holes in the 1 st row to the 5 th row, the standard gas film holes in the 6 th row to the 10 th row and the standard gas film holes in the 11 th row to the 15 th row are 4.5mm, and the longitudinal spacing is 8mm.
A threaded hole is provided at the corner of the first, second and third substrates 1, 2, 3 for connection with a measuring device.
The standard arrangement and the coordinate system of the standard component formed by the first substrate 1, the second substrate 2 and the third substrate 3 are shown in fig. 3, the standard is established by adopting the planes of the first substrate 1, the second substrate 2 and the third substrate 3 which are mutually perpendicular, the coordinate system is further established, the planeness of the three planes is 0.01mm, the perpendicularity between the three planes is 0.01mm, the position of 90 holes relative to the planes is 0.01mm, the axes of the 1 st to 5 th row standard gas film holes are perpendicular to an XOY plane, the axes of the 6 th to 10 th row standard gas film holes are perpendicular to a YOZ plane, and the axes of the 11 th to 15 th row standard gas film holes are perpendicular to the XOZ plane.
The standard component for calibrating the high-pressure turbine working vane gas film hole measuring equipment can be used for calibrating the measuring equipment, and two connecting rod structures are designed for connecting a turntable of the measuring equipment.
The first connecting rod structure is shown in fig. 4, a straight rod connecting rod 4 is adopted, the diameter of the straight rod connecting rod 4 is 10mm, the length of the straight rod connecting rod is 160mm, when the measuring device is applied, one end of the straight rod connecting rod 4 is in threaded connection with the corner position of the three perpendicular base plates of the standard piece for measuring the gas film holes of the high-pressure turbine working blades, and the other end of the straight rod connecting rod is connected with a turntable of the measuring device.
The second connecting rod structure is shown in fig. 5, the first connecting rod 5 and the second connecting rod 6 are adopted, the diameter of the first connecting rod 5 is 10mm, the length of the first connecting rod is 50mm, the diameter of the second connecting rod 6 is 10mm, the length of the second connecting rod is 100mm, when the gas film measuring device is applied, one end of the first connecting rod 5 is in threaded connection with the corner part of the three vertical base plates of the gas film hole measuring device calibration standard component for the high-pressure turbine working blade, the other end of the first connecting rod is connected with one end of the second connecting rod 6 through a single double-lug structure by using a screw, the other end of the second connecting rod 6 is connected with a measuring device turntable, the angle between the first connecting rod 5 and the second connecting rod 6 can be adjusted through a set screw, so that the spatial positions of the three vertical base plates are changed, and gas films Kong Moni with different spatial positions are realized.
In order to calibrate the standard component for calibrating the high-pressure turbine working vane air film hole measuring equipment, the invention also provides a calibrating method, wherein the measuring equipment is a composite coordinate measuring machine 7, and the composite coordinate measuring machine 7 is provided with various contact and non-contact sensors such as an optical fiber measuring sensor and the like, and can be used for detecting the micro size.
The calibration method of the standard component for calibrating the high-pressure turbine rotor blade gas film hole measuring equipment, see fig. 7, comprises the following steps:
a calibration preparation step, namely placing a standard component for calibrating the high-pressure turbine rotor blade air film hole measuring equipment on a workbench of a compound coordinate measuring machine 7, wherein a third substrate 3 is horizontally upwards as shown in fig. 6;
a reference surface measuring step of measuring the planes of the first substrate 1, the second substrate 2 and the third substrate 3 by adopting a probe sensor of a compound coordinate measuring machine 7;
a measurement coordinate system construction step, namely, taking the plane normal direction of the second substrate 2 as an X axis, the plane normal direction of the third substrate 3 as a Y axis, taking the plane normal direction of the first substrate 1 as a Z axis, and taking the intersection points of the planes of the first substrate 1, the second substrate 2 and the third substrate 3 as an origin to construct a measurement coordinate system;
a coordinate fitting step, namely introducing a standard part three-dimensional model for calibrating the high-pressure turbine working blade air film hole measuring equipment into a composite coordinate measuring machine 7, and fitting a model coordinate system and a measuring coordinate system;
a digital-analog guiding optical fiber measuring step, namely calling a composite coordinate measuring machine 7, programming a measuring program according to digital-analog guiding, completing the measurement of each row of standard air film holes on the third substrate 3, adjusting the first substrate 1 to be horizontally upwards, completing the measurement of each row of standard air film holes on the first substrate 1, adjusting the second substrate 2 to be horizontally upwards, and completing the measurement of each row of standard air film holes on the second substrate 2;
and a calibration and correction step, namely comparing measured values of the diameter, cylindricity and position degree of each row of standard air film holes with design values, and calculating correction errors.
The calibration method of the standard component for calibrating the gas film hole of the high-pressure turbine working blade disclosed by the embodiment uses the correction error of the standard component for calibrating the gas film hole of the high-pressure turbine working blade, which is obtained by the calibration of the compound coordinate measuring machine 7, and is used for calibrating other gas film hole measuring equipment, so that the precision and the capability of measuring the gas film hole of the measuring equipment can be verified, the calibration method has higher calibration efficiency and strong operability, the measuring equipment can be ensured to be used for detecting the subsequent gas film hole, a turntable of the calibration equipment is not required in the calibration process, and the measurement uncertainty of the calibration result does not comprise components caused by the turntable error, thereby having higher traceability value.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (5)
1. The utility model provides a high pressure turbine rotor blade air film hole calibration standard component for measuring equipment which characterized in that includes:
the first base plate (1) is provided with a standard leaf basin curved surface, and the standard leaf basin curved surface is provided with 1 st-5 th row of standard air film holes;
the second substrate (2) is arranged vertically to the first substrate (1), and is provided with a standard blade back curved surface, and the standard blade back curved surface is provided with 6 th-10 th rows of standard air film holes;
the third substrate (3) is vertically arranged with the first substrate (1) and the second substrate (2), and is provided with a standard front edge curved surface, and the standard front curved surface is provided with 11 th-15 th row standard air film holes;
each row of standard air film holes is provided with 6 standard air film holes which are vertical to the plane of the substrate;
the diameters of the 1 st, 3 rd, 5 th, 6 th, 8 th, 10 th, 11 th, 13 th and 15 th standard air film holes are all 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm;
the diameters of the standard air film holes in the rows 2, 4, 7, 9, 12 and 14 are all 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm;
the transverse spacing of the standard gas film holes in the 1 st row to the 5 th row, the standard gas film holes in the 6 th row to the 10 th row and the standard gas film holes in the 11 th row to the 15 th row are 4.5mm, and the longitudinal spacing is 8mm.
2. The calibration standard for a high-pressure turbine rotor blade gas film hole measuring apparatus according to claim 1, wherein,
the flatness of the first substrate (1), the second substrate (2) and the third substrate (3) is 0.01mm, and the verticality between the first substrate and the second substrate is 0.01mm;
the position degree of each row of standard air film holes relative to the substrate is 0.01mm.
3. The calibration standard for a high-pressure turbine rotor blade gas film hole measuring apparatus according to claim 1, wherein,
further comprises:
and one end of the straight rod connecting rod (4) is in threaded connection with the corner parts of the first substrate (1), the second substrate (2) and the third substrate (3), and the other end of the straight rod connecting rod is connected with the turntable of the measuring equipment.
4. The calibration standard for a high-pressure turbine rotor blade gas film hole measuring apparatus according to claim 1, wherein,
further comprises:
one end of the first connecting rod (5) is in threaded connection with the corner parts of the first base plate (1), the second base plate (2) and the third base plate (3);
and one end of the second connecting rod (6) is connected with the other end of the first connecting rod (5) through a single-double-lug structure by utilizing a screw, and the other end of the second connecting rod is connected with a turntable of the measuring equipment.
5. The method for calibrating the standard component for calibrating the high-pressure turbine working vane gas film hole measuring equipment is characterized by comprising the following steps of:
a calibration preparation step, namely placing a standard component for calibrating the high-pressure turbine rotor blade air film hole measuring equipment on a workbench of a compound coordinate measuring machine (7), wherein a third substrate (3) is horizontally upwards;
a reference surface measuring step, namely measuring planes of the first substrate (1), the second substrate (2) and the third substrate (3) by adopting a probe sensor of a compound coordinate measuring machine (7);
a measurement coordinate system construction step, namely, taking the plane normal direction of the second substrate (2) as an X axis, the plane normal direction of the third substrate (3) as a Y axis, taking the plane normal direction of the first substrate (1) as a Z axis, and taking the intersection points of the planes of the first substrate (1), the second substrate (2) and the third substrate (3) as an origin to establish a measurement coordinate system;
a coordinate fitting step, namely introducing a standard part three-dimensional model for calibrating the high-pressure turbine working blade air film hole measuring equipment into a compound coordinate measuring machine (7), and fitting a model coordinate system and a measuring coordinate system;
a digital-analog guiding optical fiber measuring step, calling a compound coordinate measuring machine (7), programming a measuring program according to digital-analog guiding, completing the measurement of each row of standard air film holes on the third substrate (3), and
adjusting the first substrate (1) to be horizontally upwards to finish measurement of each row of standard air film holes on the first substrate (1), and adjusting the second substrate (2) to be horizontally upwards to finish measurement of each row of standard air film holes on the second substrate (2);
and a calibration and correction step, namely comparing measured values of the diameter, cylindricity and position degree of each row of standard air film holes with design values, and calculating correction errors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310550808.6A CN116448026A (en) | 2023-05-16 | 2023-05-16 | Standard component and method for calibrating high-pressure turbine working blade gas film hole measuring equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310550808.6A CN116448026A (en) | 2023-05-16 | 2023-05-16 | Standard component and method for calibrating high-pressure turbine working blade gas film hole measuring equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116448026A true CN116448026A (en) | 2023-07-18 |
Family
ID=87133879
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310550808.6A Pending CN116448026A (en) | 2023-05-16 | 2023-05-16 | Standard component and method for calibrating high-pressure turbine working blade gas film hole measuring equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116448026A (en) |
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2023
- 2023-05-16 CN CN202310550808.6A patent/CN116448026A/en active Pending
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