Standard piece for calibration of a high-pressure turbine blade film hole measuring device and method thereof

Abstract

The application relates to a standard piece for calibrating a high-pressure turbine blade film hole measuring device and a method thereof, wherein the standard piece comprises a standard blade, which is a hollow structure and is provided with first to fourth column standard film holes on a blade basin surface and fifth to ninth column standard film holes on a blade back surface; wherein the first and fourth column standard film holes have a diameter of 0.3 mm, an upper tolerance of 0.01 mm, a lower tolerance of 0 mm and a cylindricity of 0.005 mm; the second and third column standard film holes have a diameter of 0.4 mm, an upper tolerance of 0.01 mm, a lower tolerance of 0 mm and a cylindricity of 0.005 mm; the fifth, eighth and ninth column standard film holes have a diameter of 0.3 mm, an upper tolerance of 0.01 mm, a lower tolerance of 0 mm and a cylindricity of 0.005 mm; the sixth and seventh column standard film holes have a diameter of 0.4 mm, an upper tolerance of 0.01 mm, a lower tolerance of 0 mm and a cylindricity of 0.005 mm; a rim plate is in the shape of a parallelogram and is connected to the root of the standard blade on the upper surface; a cylinder has a diameter of 10 mm and a length of 40 mm, is connected to the lower surface of the rim plate at one end and is connected to a measuring device turntable at the other end.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of engine high-pressure turbine blade film hole measurement, and particularly relates to a standard part for calibrating a high-pressure turbine blade film hole measurement device and a method thereof. BACKGROUND

[0002] With the rapid development of engine technology, the temperature resistance requirement of high-pressure turbine blades is also higher and higher. Therefore, film holes are arranged on the surface of high-pressure turbine blades to cool the high-pressure turbine blades. The distribution of the film holes on the high-pressure turbine blades is shown in FIG. 1, and the film holes on the high-pressure turbine blades are numerous, small in diameter and complex in spatial distribution. Precise measurement of the film holes on the high-pressure turbine blades is a prerequisite for objective evaluation of the film holes on the high-pressure turbine blades. Figure 1

[0003] Currently, when measuring the film holes on the high-pressure turbine blades of an engine, repeated measurements are performed by using a measurement device. However, there is a lack of calibration means for measuring accuracy of the measurement device, and the accuracy of the measurement of the film holes on the high-pressure turbine blades cannot be ensured, so the processing quality of the film holes on the high-pressure turbine blades cannot be accurately evaluated.

[0004] The present application is proposed in view of the above technical defects.

[0005] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The purpose of the present application is to provide a standard part for calibrating a high-pressure turbine blade film hole measurement device and a method thereof, so as to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is:

[0008] In one aspect, a standard part for calibrating a high-pressure turbine blade film hole measurement device is provided, comprising:

[0009] ​The standard blade is a hollow structure, and has 1st-4th standard air film holes on the blade basin surface and 5th-9th standard air film holes on the blade back surface; the longitudinal distance of each column of standard air film holes is 8mm, wherein the diameter of the 1st and 4th standard air film holes is 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameter of the 2nd and 3rd standard air film holes is 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameter of the 5th, 8th and 9th standard air film holes is 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameter of the 6th and 7th standard air film holes is 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm;

[0010] The edge plate is in the shape of a parallelogram, and the upper surface is connected to the root of the standard blade;

[0011] The cylinder has a diameter of 10mm and a length of 40mm, and is connected to the lower surface of the edge plate at one end and to the turntable of the measuring equipment at the other end.

[0012] Optionally, in the standard piece for calibrating the high-pressure turbine blade air film hole measuring equipment, the straightness of the axis of the cylinder is 0.01mm;

[0013] The flatness of the lower surface of the edge plate is 0.01mm;

[0014] The flatness of the two sides of the edge plate is 0.01mm.

[0015] Optionally, in the standard piece for calibrating the high-pressure turbine blade air film hole measuring equipment, the axis of the cylinder is the Z axis, the normal line of the symmetrical surface of the two sides of the edge plate is the X axis, the intersection of the axis of the cylinder and the lower surface of the edge plate is the origin, and the Y axis passes through the origin and is perpendicular to the X axis and the Z axis;

[0016] The angle between the axis of the 1st standard air film hole and the XOY plane is 50 degrees, and the included angle with the positive direction of the X axis is 60 degrees;

[0017] The angle between the axis of the 2nd standard air film hole and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 70 degrees;

[0018] The angle between the axis of the 3rd standard air film hole and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 90 degrees;

[0019] The angle between the axis of the 4th standard air film hole and the XOY plane is 30 degrees, and the included angle with the positive direction of the X axis is 140 degrees;

[0020] The angle between the axis of the 5th standard air film hole and the XOY plane is 30 degrees, and the included angle with the positive direction of the X axis is 50 degrees;

[0021] The angle between the axis of the standard gas film hole in column 6 and the XOY plane is 20 degrees, and the angle between the axis and the positive direction of the X axis is 35 degrees;

[0022] The angle between the axis of the standard gas film hole in column 7 and the XOY plane is 0 degrees, and the angle between the axis and the positive direction of the X axis is 75 degrees;

[0023] The angle between the axis of the standard gas film hole in column 8 and the XOY plane is 40 degrees, and the angle between the axis and the positive direction of the X axis is 100 degrees;

[0024] The angle between the axis of the standard gas film hole in column 9 and the XOY plane is 40 degrees, and the angle between the axis and the positive direction of the X axis is 120 degrees.

[0025] In another aspect, a standard calibration method for calibrating a high-pressure turbine blade gas film hole measuring device is provided, comprising:

[0026] The calibration fixture fixing step is to connect a cylinder to a double-axis turntable of a compound coordinate measuring machine, and to fix the standard for calibrating the high-pressure turbine blade gas film hole measuring device;

[0027] The workpiece coordinate system establishing step is to measure three circles on the cylinder by using a probe sensor of the compound coordinate measuring machine, to obtain the axis of the cylinder by fitting, to take the axis as the Z axis, to measure the lower surface of the rim plate by using the probe sensor of the compound coordinate measuring machine, to measure two side surfaces of the rim plate by using the probe sensor of the compound coordinate measuring machine, to obtain the symmetry plane, to take the normal line of the symmetry plane as the X axis, and to take the intersection of the axis of the cylinder and the lower surface of the rim plate as the origin, and to take the Y axis to pass through the origin, perpendicular to the X axis and the Z axis, to construct the workpiece coordinate;

[0028] The coordinate system fitting step is to import a three-dimensional model of the standard for calibrating the high-pressure turbine blade gas film hole measuring device into the compound coordinate measuring machine, and to fit the model coordinate system with the workpiece coordinate system;

[0029] The digital model guided optical fiber measurement step is to call the optical fiber sensor of the compound coordinate measuring machine, to compile a measurement program according to the digital model guidance, and to complete the measurement of each column of standard gas film holes on the standard blade;

[0030] The calibration correction step is to compare the measured values of the diameters, cylindricity and position of each column of standard gas film holes with the design values, and to calculate the correction error. BRIEF DESCRIPTION OF DRAWINGS

[0031] Figure 1 is a schematic diagram of the distribution of the gas film holes of the high-pressure turbine blade of the existing engine;

[0032] Figure 2 is a schematic diagram of the standard for calibrating the high-pressure turbine blade gas film hole measuring device provided by the embodiment of the application;

[0033] Figure 3A standard part coordinate system construction schematic diagram for calibrating a high-pressure turbine blade film hole measuring device is provided in the embodiments of the present application.

[0034] Figure 4 A standard part calibration method schematic diagram for calibrating a high-pressure turbine blade film hole measuring device is provided in the embodiments of the present application.

[0035] Figure 5 A standard part calibration method flow chart for calibrating a high-pressure turbine blade film hole measuring device is provided in the embodiments of the present application.

[0036] Wherein:

[0037] 1-standard blade; 2-rib; 3-cylinder; 4-composite coordinate measuring machine.

[0038] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and in addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0039] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0040] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as the common meaning understood by one of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application only indicate relative directions or positional relationships, and do not imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional relationship may also change accordingly when the absolute position of the described object changes, therefore it cannot be understood as a limitation on the present application. The "first", "second", "third" and the like used in the description of the present application are only for the purpose of description, in order to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the quantity, but should be understood as the presence of at least one. The "includes" or "contains" and the like used in the description of the present application means that the elements or objects appearing before the word are covered by the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0041] In addition, it should be noted that, unless otherwise specified and limited, the "installation", "connection", "connection" and the like used in the description of the present application should be understood broadly, for example, the connection can be fixed connection, or detachable connection, or integral connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal communication of two elements, and those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0042] The following will be described in detail in combination with the accompanying drawings Figures 1 to 5 The present application is further described in detail.

[0043] The embodiment of the present application provides a standard part for calibrating a high-pressure turbine blade film hole measuring device, which is simple in structure, easy to realize, high in shape and position tolerance accuracy of the reference and the film hole, can simulate the shape and position parameters of the film hole on the real blade, realize the simulation of the film hole with different diameters, different axis angles and different spatial positions, calibrate through a high-precision measuring device, and can be used for calibrating the film hole measuring device after calibration, and can meet the calibration of the film hole measuring device under various conditions.

[0044] The structure of the standard part for calibrating the high-pressure turbine blade film hole measuring device is shown in Figure 2 The standard part for calibrating the high-pressure turbine blade film hole measuring device is shown in

[0045] The standard blade 1 has 9 columns of standard film holes, the standard film holes are through holes, each column has 6 standard film holes, a total of 54, the longitudinal spacing of each column of standard film holes is 8mm, wherein the first to fourth columns of standard film holes are located on the blade pressure surface, and the fifth to ninth columns of standard film holes are located on the blade suction surface.

[0046] The diameters of the first and fourth columns of standard 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 second and third columns of standard 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 fifth, eighth and ninth columns of standard 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 sixth and seventh columns of standard film holes are 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm.

[0047] The standard blade 1 is connected to the upper surface of the rim plate 2, the rim plate 2 is a parallelogram, the lower surface of the rim plate 2 is connected to one end of the cylinder 3, the other end of the cylinder 3 is used to connect with the turntable of the measuring equipment, the diameter of the cylinder 3 is 10mm, and the length is 40mm.

[0048] The reference setting of the standard piece for calibrating the high-pressure turbine blade film hole measuring equipment is as shown in Figure 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 rim plate 2, the flatness is 0.01mm, and the reference C is the two side surfaces of the rim plate 2, the flatness is 0.01mm. The reference A is set as the Z axis, the normal line of the symmetry plane of the reference is set as the X axis, the intersection point of the reference A cylinder axis and the reference B plane is set as the X, Y, Z origin, and the coordinate system is constructed.

[0049] The angle between the axis of the first column of standard film holes and the XOY plane is 50 degrees, and the included angle with the positive direction of the X axis is 60 degrees; the angle between the axis of the second column of standard film holes and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 70 degrees; the angle between the axis of the third column of standard film holes and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 90 degrees; the angle between the axis of the fourth column of standard film holes and the XOY plane is 30 degrees, and the included angle with the positive direction of the X axis is 140 degrees; the angle between the axis of the fifth column of standard film holes and the XOY plane is 30 degrees, and the included angle with the positive direction of the X axis is 50 degrees; the angle between the axis of the sixth column of standard film holes and the XOY plane is 20 degrees, and the included angle with the positive direction of the X axis is 35 degrees; the angle between the axis of the seventh column of standard film holes and the XOY plane is 0 degrees, and the included angle with the positive direction of the X axis is 75 degrees; the angle between the axis of the eighth column of standard film holes and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 100 degrees; the angle between the axis of the ninth column of standard film holes and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 120 degrees.

[0050] In order to calibrate the motive high-pressure turbine blade film hole measuring calibration piece, relying on the composite coordinate measuring machine, the application embodiment provides a kind of calibration method, composite coordinate measuring machine is equipped with multiple contact and non-contact sensors such as fiber measurement sensor, can be used for the detection of small size.

[0051] The standard piece calibration method for high-pressure turbine blade film hole measuring equipment calibration, see Figure 5 , comprising:

[0052] Calibration piece clamping and fixing step, connect cylinder 3 to the double-axis turntable of composite coordinate measuring machine 4, and clamp and fix the standard piece for high-pressure turbine blade film hole measuring equipment calibration, as shown in Figure 4 ;

[0053] Workpiece coordinate system establishment step, the axis A of cylinder 3 is obtained by fitting three circles measured on cylinder 3 by composite coordinate measuring machine 4 probe sensor, as Z axis, the lower surface B of rim plate 2 is measured by composite coordinate measuring machine 4 probe sensor, two side surfaces C of rim plate 2 are measured by composite coordinate measuring machine 4 probe sensor, the symmetry plane is calculated, the normal line of symmetry plane is taken as X axis, the intersection of the axis A of cylinder 3 and the lower surface B of rim plate 2 is taken as origin, Y axis is set through origin, perpendicular to X axis and Z axis, and workpiece coordinate is constructed;

[0054] Coordinate system fitting step, the three-dimensional model of the standard piece for high-pressure turbine blade film hole measuring equipment calibration is imported into composite coordinate measuring machine 4, and the model coordinate system is fitted with workpiece coordinate system;

[0055] Digital model guided fiber measurement step, composite coordinate measuring machine 4 fiber sensor is called, measurement program is prepared according to digital model guidance, and each column of standard film hole on standard blade 1 is measured;

[0056] Calibration correction step, the diameter, cylindricity and position degree measurement values of each column of standard film hole are compared with design values, and correction error is calculated.

[0057] The standard piece calibration method for high-pressure turbine blade film hole measuring equipment calibration disclosed in the above embodiment has strong operability, the calibration piece is calibrated by composite coordinate measuring machine, the calibrated calibration piece can calibrate other measuring equipment, and has high calibration efficiency.

[0058] The application designs a high-precision blade film hole standard piece structure for film hole calibration, solves the problems that current film hole measuring equipment cannot be calibrated and measurement precision of measurement equipment cannot be verified.

[0059] The various embodiments described in the specification are intended to be exemplary only and are not intended to limit the scope of the application. The scope of the application is defined by the claims.

[0060] The technical solutions of the present application have been described in combination with the preferred embodiments shown in the drawings. It should be understood by those skilled in the art that the protection scope of the present application is obviously not limited to these specific embodiments. Those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application. The technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A standard piece for calibration of a high-pressure turbine blade film hole measuring apparatus, characterized by, It comprises: Standard blade (1), hollow structure, and the tip opening, the first to the fourth column standard film holes on the blade basin surface, the fifth to the ninth column standard film holes on the blade back surface; the longitudinal spacing of each column standard film hole is 8mm, wherein the diameter of the first and fourth column standard film holes is 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameter of the second and third column standard film holes is 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameter of the fifth, eighth and ninth column standard film holes is 0.3mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; the diameter of the sixth and seventh column standard film holes is 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; The rim plate (2) is in the shape of a parallelogram, and the upper surface is connected to the root of the standard blade (1); The cylinder (3) has a diameter of 10mm and a length of 40mm, one end is connected to the lower surface of the rim plate (2), and the other end is connected to the measuring equipment turntable; The axis (A) of the cylinder (3) is the Z axis, the normal line of the symmetric plane of the two side surfaces (C) of the rim plate (2) is the X axis, and the intersection of the axis (A) of the cylinder (3) and the lower surface (B) of the rim plate (2) is the origin, and the Y axis passes through the origin and is perpendicular to the X and Z axes; The angle between the axis of the first column standard film hole and the XOY plane is 50 degrees, and the included angle with the positive direction of the X axis is 60 degrees; The angle between the axis of the second column standard film hole and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 70 degrees; The angle between the axis of the third column standard film hole and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 90 degrees; The angle between the axis of the fourth column standard film hole and the XOY plane is 30 degrees, and the included angle with the positive direction of the X axis is 140 degrees; The angle between the axis of the fifth column standard film hole and the XOY plane is 30 degrees, and the included angle with the positive direction of the X axis is 50 degrees; The angle between the axis of the sixth column standard film hole and the XOY plane is 20 degrees, and the included angle with the positive direction of the X axis is 35 degrees; The angle between the axis of the seventh column standard film hole and the XOY plane is 0 degrees, and the included angle with the positive direction of the X axis is 75 degrees; The angle between the axis of the eighth column standard film hole and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 100 degrees; The angle between the axis of the ninth column standard film hole and the XOY plane is 40 degrees, and the included angle with the positive direction of the X axis is 120 degrees.

2. The standard piece for calibrating the high-pressure turbine blade film hole measuring device 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 rim plate (2) is 0.01mm; The flatness of the two side surfaces (C) of the rim plate (2) is 0.01mm. The standard piece for calibrating the high-pressure turbine blade film hole measuring device based on claim 2 comprises:

3. A method of calibrating a standard for calibration of a high pressure turbine vane film hole measurement apparatus, the method comprising: providing a standard having a plurality of film holes; and measuring a film hole diameter of each of the plurality of film holes of the standard using a film hole diameter measurement device. The standard piece for calibrating the high-pressure turbine blade film hole measuring device is clamped and fixed by connecting the cylinder (3) to the double-axis turntable of the composite coordinate measuring machine (4). ​ The workpiece coordinate system establishing step is to measure three circles on the cylinder (3) by the probe sensor of the compound coordinate measuring machine (4), to obtain the axis (A) of the cylinder (3) by fitting, as the Z axis, to measure the lower surface (B) of the rim plate (2) by the probe sensor of the compound coordinate measuring machine (4), to measure the two side surfaces (C) of the rim plate (2) by the probe sensor of the compound coordinate measuring machine (4), to obtain the symmetry plane, to take the normal of the symmetry plane as the X axis, to take the intersection of the axis (A) of the cylinder (3) and the lower surface (B) of the rim plate (2) as the origin, to take the Y axis through the origin, perpendicular to the X axis and the Z axis, and to construct the workpiece coordinate system; The coordinate system fitting step is to import the three-dimensional model of the standard piece for calibrating the high-pressure turbine blade film hole measuring equipment into the compound coordinate measuring machine (4), to fit the model coordinate system and the workpiece coordinate system; The digital model guiding optical fiber measuring step is to call the optical fiber sensor of the compound coordinate measuring machine (4), to compile a measuring program according to digital model guiding, and to complete the measurement of each column of standard film holes on the standard blade (1); The calibration correction step is to compare the measured values of the diameters, cylindricity and position of each column of standard film holes with the design values, and to calculate the correction error.

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