CN116608807A - Standard component for calibrating high-pressure turbine blade air film hole measuring equipment and method thereof - Google Patents

Standard component for calibrating high-pressure turbine blade air film hole measuring equipment and method thereof Download PDF

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Publication number
CN116608807A
CN116608807A CN202310550807.1A CN202310550807A CN116608807A CN 116608807 A CN116608807 A CN 116608807A CN 202310550807 A CN202310550807 A CN 202310550807A CN 116608807 A CN116608807 A CN 116608807A
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China
Prior art keywords
axis
air film
row
standard
film holes
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CN202310550807.1A
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Chinese (zh)
Inventor
闫峰
高继昆
王荣誉
何小妹
张涛
德晓薇
李季
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AECC Shenyang Engine Research Institute
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AECC Shenyang Engine Research Institute
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Priority to CN202310550807.1A priority Critical patent/CN116608807A/en
Publication of CN116608807A publication Critical patent/CN116608807A/en
Pending legal-status Critical Current

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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)
  • Length Measuring Devices With Unspecified Measuring Means (AREA)

Abstract

The application relates to a standard component for calibrating high-pressure turbine blade air film hole measuring equipment and a method thereof, wherein the standard component comprises the following components: the standard blade is of a hollow structure, the surface of the blade basin is provided with 1 st to 4 th rows of standard air film holes, and the back surface of the blade is provided with 5 th to 9 th rows of standard air film holes; the diameters of the 1 st and 4 th rows of standard air film holes are 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 2 nd row and the 3 rd row of standard air film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 5 th, 8 th and 9 th rows of standard air film holes are 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 6 th and 7 th rows of standard air film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the edge plate is in a parallelogram shape, and the upper surface of the edge plate is connected with the root of the standard blade; the diameter of the cylinder is 10mm, the length of the cylinder is 40mm, one end of the cylinder is connected to the lower surface of the flange plate, and the other end of the cylinder is connected to the turntable of the measuring equipment.

Description

Standard component for calibrating high-pressure turbine blade air film hole measuring equipment and method thereof
Technical Field
The application belongs to the field of measurement of gas film holes of high-pressure turbine blades of engines, and particularly relates to a standard component for calibration of gas film holes of high-pressure turbine blades and a method thereof.
Background
Along with the rapid development of engine technology, the requirements on the temperature bearing capacity of the high-pressure turbine blade are higher and higher, therefore, the air film holes are formed in the surface of the high-pressure turbine blade, the high-pressure turbine blade is cooled, the air film holes in the high-pressure turbine blade are distributed as shown in the figure 1, the number of the air film holes in the high-pressure turbine blade is large, the diameter is small, the space distribution is complex, the air film holes in the high-pressure turbine blade are precisely measured, and the air film holes in the high-pressure turbine blade can be objectively evaluated.
At present, when measuring the gas film hole on the high-pressure turbine blade of the engine, repeated measurement is carried out by using measuring equipment, but a calibration means for measuring the accuracy of the measuring equipment is lacked, the accuracy of measuring the gas film hole on the high-pressure turbine blade cannot be ensured, and the processing quality of the gas film hole on the high-pressure turbine blade cannot be accurately evaluated.
The present application has been made in view of the above-described 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 application, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the inventive idea of the present application in the case where no clear evidence indicates that the above-mentioned content is already disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide a standard part for calibrating high-pressure turbine blade gas film hole measuring equipment and a method thereof, which overcome or alleviate the technical defects of at least one aspect of the known technology.
The technical scheme of the application is as follows:
in one aspect, a standard for calibrating high pressure turbine blade gas film hole measurement equipment is provided, comprising:
the standard blade is of a hollow structure, the surface of the blade basin is provided with 1 st to 4 th rows of standard air film holes, and the back surface of the blade is provided with 5 th to 9 th rows of standard air film holes; the longitudinal distance between the standard gas film holes in each row is 8mm, wherein the diameters of the standard gas film holes in the 1 st row and the 4 th row are 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 2 nd row and the 3 rd row of standard air film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 5 th, 8 th and 9 th rows of standard air film holes are 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 6 th and 7 th rows of standard air film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm;
the edge plate is in a parallelogram shape, and the upper surface of the edge plate is connected with the root of the standard blade;
the diameter of the cylinder is 10mm, the length of the cylinder is 40mm, one end of the cylinder is connected to the lower surface of the flange plate, and the other end of the cylinder is connected to the turntable of the measuring equipment.
Optionally, in the standard component for calibrating the high-pressure turbine blade air film hole measuring device, the straightness of the axis of the cylinder is 0.01mm;
the flatness of the lower surface of the flange plate is 0.01mm;
the flatness of both sides of the rim plate was 0.01mm.
Optionally, in the standard component for calibrating the high-pressure turbine blade air film hole measuring device, the axis of the cylinder is taken as a Z axis, the normal lines of the symmetrical planes of the two side surfaces of the flange plate are taken as an X axis, the intersection point of the axis of the cylinder and the lower surface of the flange plate is taken as an origin, and the Y axis passes through the origin and is perpendicular to the X axis and the Z axis;
the angle between the axis of the 1 st row of standard air film holes and the XOY plane is 50 degrees, and the positive angle between the axis of the 1 st row of standard air film holes and the X axis is 60 degrees;
the angle between the axis of the 2 nd row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 2 nd row of standard air film holes and the X axis is 70 degrees;
the angle between the axis of the 3 rd row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 3 rd row of standard air film holes and the X axis is 90 degrees;
the angle between the axis of the 4 th row of standard air film holes and the XOY plane is 30 degrees, and the positive angle between the axis of the 4 th row of standard air film holes and the X axis is 140 degrees;
the angle between the axis of the 5 th row of standard air film holes and the XOY plane is 30 degrees, and the positive angle between the axis of the 5 th row of standard air film holes and the X axis is 50 degrees;
the angle between the axis of the 6 th row of standard air film holes and the XOY plane is 20 degrees, and the positive included angle between the axis of the 6 th row of standard air film holes and the X axis is 35 degrees;
the angle between the axis of the 7 th row of standard air film holes and the XOY plane is 0 degree, and the positive angle between the axis of the 7 th row of standard air film holes and the X axis is 75 degrees;
the angle between the axis of the 8 th row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 8 th row of standard air film holes and the X axis is 100 degrees;
the angle between the axis of the 9 th row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 9 th row of standard air film holes and the X axis is 120 degrees.
In another aspect, a method for calibrating a standard component for calibrating a high-pressure turbine blade gas film hole measurement device is provided, including:
clamping and fixing the calibration piece, namely connecting a cylinder to a double-shaft turntable of a compound coordinate measuring machine, and clamping and fixing a standard piece for calibrating high-pressure turbine blade air film hole measuring equipment;
a step of establishing a workpiece coordinate system, in which three circles are measured on a cylinder by a probe sensor of a compound coordinate measuring machine, the axis of the cylinder is obtained through fitting, the axis is taken as a Z axis, the lower surface of a flange plate is measured by the probe sensor of the compound coordinate measuring machine, two side surfaces of the flange plate are measured by the probe sensor of the compound coordinate measuring machine, a symmetrical plane is obtained, a normal line of the symmetrical plane is taken as an X axis, an intersection point of the axis of the cylinder and the lower surface of the flange plate is taken as an origin, a Y axis is set to pass through the origin and is perpendicular to the X axis and the Z axis, and workpiece coordinates are constructed;
a coordinate system fitting step, namely introducing a three-dimensional model of a standard component for calibrating high-pressure turbine blade air film hole measuring equipment into a composite coordinate measuring machine, and fitting a model coordinate system and a workpiece coordinate system;
a digital-analog guiding optical fiber measuring step, namely calling an optical fiber sensor of the composite coordinate measuring machine, and programming a measuring program according to digital-analog guiding to finish the measurement of each row of standard air film holes on the standard blade;
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 high-pressure turbine blade of a prior engine;
FIG. 2 is a schematic diagram of a standard for calibration of high pressure turbine blade gas film hole measurement equipment provided by an embodiment of the present application;
FIG. 3 is a schematic diagram of the coordinate system construction of a standard component for calibrating a high-pressure turbine blade gas film hole measuring device provided by the embodiment of the application;
FIG. 4 is a schematic diagram of a calibration method for a standard component for calibrating high-pressure turbine blade gas film hole measurement equipment provided by an embodiment of the application;
FIG. 5 is a flowchart of a method for calibrating a standard component for calibrating high-pressure turbine blade gas film hole measurement equipment, provided by an embodiment of the application;
wherein:
1-standard blades; 2-a flange plate; 3-cylinder; 4-compound coordinate measuring machine.
For the purpose of better illustrating the embodiments, certain elements of the drawings are omitted, enlarged or reduced in size and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the application.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail 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 and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, 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 application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; 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 application is described in further detail below with reference to fig. 1 to 5.
The embodiment of the application provides a standard component for calibrating high-pressure turbine blade air film hole measuring equipment, which has the advantages of simple structure, easiness in realization and high accuracy of geometric tolerance of a standard and air film holes, can simulate geometric parameters of the air film holes on a real blade, realizes simulation of the air film holes with different diameters, different coaxial angles and different spatial positions, can be used for calibrating the air film hole measuring equipment after being calibrated through the high-accuracy measuring equipment, and can meet the calibration of the air film hole measuring equipment under various conditions.
The standard component structure for calibrating the high-pressure turbine blade air film hole measuring equipment is shown in fig. 2, and comprises a standard blade 1, a flange plate 2 and a cylinder 3.
The standard vane 1 is provided with 9 rows of standard air film holes, the standard air film holes are through holes, each row of standard air film holes is provided with 6, the total number of the standard air film holes is 54, the longitudinal distance between the standard air film holes in each row is 8mm, wherein the 1 st to 4 th rows of standard air film holes are positioned on the surface of the vane basin, and the 5 th to 9 th rows of standard air film holes are positioned on the back surface of the vane.
The diameters of the 1 st and 4 th rows of standard air film holes are 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 2 nd row and the 3 rd row of standard air film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 5 th, 8 th and 9 th rows of standard air film holes are 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm. The diameters of the 6 th row and the 7 th row of standard air film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm.
The root of the standard blade 1 is connected to the upper surface of the flange plate 2, the flange plate 2 is in a parallelogram shape, the lower surface of the flange plate is connected with one end of a cylinder 3, the other end of the cylinder 3 is used for being connected with a turntable of measuring equipment, the diameter of the cylinder 3 is 10mm, and the length of the cylinder 3 is 40mm.
The reference setting of the standard component for calibrating the high-pressure turbine blade air film hole measuring equipment is shown in fig. 3, the reference A is the axis of the cylinder 3, the straightness of the axis of the cylinder 3 is 0.01mm, the reference B is the lower surface of the flange plate 2, the flatness is 0.01mm, the reference C is two side surfaces of the flange plate 2, and the flatness is 0.01mm. The reference a was set as the Z axis, the normal line of the symmetry plane of the reference was set as the X axis, the intersection point of the reference a cylindrical axis and the reference B plane was established, and the point was set as the X, Y, Z origin, and a coordinate system was constructed.
The angle between the axis of the 1 st row of standard air film holes and the XOY plane is 50 degrees, and the positive angle between the axis of the 1 st row of standard air film holes and the X axis is 60 degrees; the angle between the axis of the 2 nd row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 2 nd row of standard air film holes and the X axis is 70 degrees; the angle between the axis of the 3 rd row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 3 rd row of standard air film holes and the X axis is 90 degrees; the angle between the axis of the 4 th row of standard air film holes and the XOY plane is 30 degrees, and the positive angle between the axis of the 4 th row of standard air film holes and the X axis is 140 degrees; the angle between the axis of the 5 th row of standard air film holes and the XOY plane is 30 degrees, and the positive angle between the axis of the 5 th row of standard air film holes and the X axis is 50 degrees; the angle between the axis of the 6 th row of standard air film holes and the XOY plane is 20 degrees, and the positive included angle between the axis of the 6 th row of standard air film holes and the X axis is 35 degrees; the angle between the axis of the 7 th row of standard air film holes and the XOY plane is 0 degree, and the positive angle between the axis of the 7 th row of standard air film holes and the X axis is 75 degrees; the angle between the axis of the 8 th row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 8 th row of standard air film holes and the X axis is 100 degrees; the angle between the axis of the 9 th row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 9 th row of standard air film holes and the X axis is 120 degrees.
In order to calibrate a gas film hole measurement calibration piece of a high-pressure turbine blade of a motor, the embodiment of the application provides a calibration method by means of a composite coordinate measuring machine, and the composite coordinate measuring machine is provided with various contact type and non-contact type sensors such as an optical fiber measurement sensor and can be used for detecting micro-size.
A method of calibration of a standard for calibration of high pressure turbine blade gas film hole measurement equipment, see fig. 5, comprising:
a calibration piece clamping and fixing step, namely connecting a cylinder 3 to a double-shaft turntable of a composite coordinate measuring machine 4, and clamping and fixing a standard piece for calibrating high-pressure turbine blade air film hole measuring equipment, as shown in fig. 4;
a step of establishing a workpiece coordinate system, in which three circles are measured on a cylinder 3 by a probe sensor of a compound coordinate measuring machine 4, an axis A of the cylinder 3 is obtained through fitting, the axis A is used as a Z axis, the lower surface B of a flange plate 2 is measured by the probe sensor of the compound coordinate measuring machine 4, two side surfaces C of the flange plate 2 are measured by the probe sensor of the compound coordinate measuring machine 4, a symmetrical plane is obtained, a normal line of the symmetrical plane is used as an X axis, an intersection point of the axis A of the cylinder 3 and the lower surface B of the flange plate 2 is used as an origin, a Y axis is set to pass through the origin, and the Y axis is perpendicular to the X axis and the Z axis, so that a workpiece coordinate is constructed;
a coordinate system fitting step, namely introducing a three-dimensional model of a standard component for calibrating high-pressure turbine blade air film hole measuring equipment into a composite coordinate measuring machine 4, and fitting a model coordinate system and a workpiece coordinate system;
a digital-analog guiding optical fiber measuring step, namely calling an optical fiber sensor of the compound coordinate measuring machine 4, and programming a measuring program according to digital-analog guiding to finish the measurement of each row of standard air film holes on the standard blade 1;
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 standard component calibration method for calibrating the high-pressure turbine blade air film hole measurement equipment disclosed by the embodiment is high in operability, the calibration component is calibrated through the combined type coordinate measuring machine, and the calibrated calibration component can calibrate other measurement equipment and has higher calibration efficiency.
The application designs a high-precision blade air film hole standard component structure for calibrating an air film hole, which solves the problems that the air film hole measuring equipment cannot be calibrated at present and the measuring equipment cannot be verified to measure the air film hole precision.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the 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 related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.

Claims (4)

1. A standard for calibrating high pressure turbine blade gas film hole measurement equipment, comprising:
the standard blade (1) is of a hollow structure, the surface of the blade basin is provided with 1 st to 4 th rows of standard air film holes, and the back surface of the blade is provided with 5 th to 9 th rows of standard air film holes; the longitudinal distance between the standard gas film holes in each row is 8mm, wherein the diameters of the standard gas film holes in the 1 st row and the 4 th row are 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 2 nd row and the 3 rd row of standard air film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 5 th, 8 th and 9 th rows of standard air film holes are 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameters of the 6 th and 7 th rows of standard air film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm;
the edge plate (2) is in a parallelogram shape, and the upper surface of the edge plate is connected with the root of the standard blade (1);
and the diameter of the cylinder (3) is 10mm, the length of the cylinder is 40mm, one end of the cylinder is connected to the lower surface of the flange plate (2), and the other end of the cylinder is connected to the turntable of the measuring equipment.
2. The standard for calibrating high-pressure turbine blade gas film hole measurement equipment according to claim 1, wherein,
the straightness of the axis (A) of the cylinder (3) is 0.01mm;
the flatness of the lower surface (B) of the flange plate (2) is 0.01mm;
the flatness of the two sides (C) of the flange (2) was 0.01mm.
3. The standard for calibrating high-pressure turbine blade gas film hole measurement equipment according to claim 1, wherein,
taking an axis (A) of the cylinder (3) as a Z axis, taking normals of symmetrical planes of two side surfaces (C) of the flange plate (2) as X axes, taking an intersection point of the axis (A) of the cylinder (3) and the lower surface (B) of the flange plate (2) as an origin, and taking a Y axis passing through the origin and being perpendicular to the X axis and the Z axis;
the angle between the axis of the 1 st row of standard air film holes and the XOY plane is 50 degrees, and the positive angle between the axis of the 1 st row of standard air film holes and the X axis is 60 degrees;
the angle between the axis of the 2 nd row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 2 nd row of standard air film holes and the X axis is 70 degrees;
the angle between the axis of the 3 rd row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 3 rd row of standard air film holes and the X axis is 90 degrees;
the angle between the axis of the 4 th row of standard air film holes and the XOY plane is 30 degrees, and the positive angle between the axis of the 4 th row of standard air film holes and the X axis is 140 degrees;
the angle between the axis of the 5 th row of standard air film holes and the XOY plane is 30 degrees, and the positive angle between the axis of the 5 th row of standard air film holes and the X axis is 50 degrees;
the angle between the axis of the 6 th row of standard air film holes and the XOY plane is 20 degrees, and the positive included angle between the axis of the 6 th row of standard air film holes and the X axis is 35 degrees;
the angle between the axis of the 7 th row of standard air film holes and the XOY plane is 0 degree, and the positive angle between the axis of the 7 th row of standard air film holes and the X axis is 75 degrees;
the angle between the axis of the 8 th row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 8 th row of standard air film holes and the X axis is 100 degrees;
the angle between the axis of the 9 th row of standard air film holes and the XOY plane is 40 degrees, and the positive angle between the axis of the 9 th row of standard air film holes and the X axis is 120 degrees.
4. A method for calibrating a standard component for calibrating high-pressure turbine blade gas film hole measurement equipment, comprising the steps of:
a calibration piece clamping and fixing step, namely connecting a cylinder (3) to a double-shaft turntable of a compound coordinate measuring machine (4), and clamping and fixing a standard piece for calibrating high-pressure turbine blade air film hole measuring equipment;
a step of establishing a workpiece coordinate system, in which three circles are measured on a cylinder (3) by using a probe sensor of a compound coordinate measuring machine (4), an axis (A) of the cylinder (3) is obtained through fitting, the axis is used as a Z axis, the lower surface (B) of a flange plate (2) is measured by using the probe sensor of the compound coordinate measuring machine (4), two side surfaces (C) of the flange plate (2) are measured by using the probe sensor of the compound coordinate measuring machine (4), a symmetrical plane is obtained, a normal line of the symmetrical plane is used as an X axis, an intersection point of the axis (A) of the cylinder (3) and the lower surface (B) of the flange plate (2) is used as an origin, a Y axis passing through the origin is arranged and is perpendicular to the X axis and the Z axis, and workpiece coordinates are constructed;
a coordinate system fitting step, namely introducing a three-dimensional model of a standard component for calibrating high-pressure turbine blade air film hole measuring equipment into a compound coordinate measuring machine (4), and fitting a model coordinate system and a workpiece coordinate system;
a digital-analog guiding optical fiber measuring step, namely calling an optical fiber sensor of a compound coordinate measuring machine (4), and programming a measuring program according to digital-analog guiding to finish the measurement of each row of standard air film holes on the standard blade (1);
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.
CN202310550807.1A 2023-05-16 2023-05-16 Standard component for calibrating high-pressure turbine blade air film hole measuring equipment and method thereof Pending CN116608807A (en)

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Application Number Priority Date Filing Date Title
CN202310550807.1A CN116608807A (en) 2023-05-16 2023-05-16 Standard component for calibrating high-pressure turbine blade air film hole measuring equipment and method thereof

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Application Number Priority Date Filing Date Title
CN202310550807.1A CN116608807A (en) 2023-05-16 2023-05-16 Standard component for calibrating high-pressure turbine blade air film hole measuring equipment and method thereof

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