Standard piece and method for calibrating high-pressure turbine working blade film hole measuring equipment

Abstract

The application belongs to the technical field of high-pressure turbine working blade film hole measurement of an aero-engine, and particularly relates to a standard piece for calibrating a high-pressure turbine working blade film hole measurement device and a method, wherein the standard piece comprises: a first base plate having a standard blade basin curved surface, the standard blade basin curved surface having 1st-5th column standard film holes; a second base plate vertically arranged with the first base plate, having a standard blade back curved surface, the standard blade back curved surface having 6th-10th column standard film holes; and a third base plate vertically arranged with the first base plate and the second base plate, having a standard leading edge curved surface, the standard leading edge curved surface having 11th-15th column standard film holes; each column of standard film holes has six standard film holes, which are perpendicular to the plane of the base plate; the horizontal spacing of the 1st-5th column standard film holes, the 6th-10th column standard film holes and the 11th-15th column standard film holes is 4.5 mm, and the longitudinal spacing is 8 mm.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of gas film hole measurement of high-pressure turbine working blades of an aero-engine, and particularly relates to a standard piece for calibrating a gas film hole measurement device of a high-pressure turbine working blade and a method. BACKGROUND

[0002] The gas film holes on the high-pressure turbine working blades of an aero-engine are of great significance to the cooling of the high-pressure turbine working blades, and the distribution of the gas film holes on the high-pressure turbine working blades is as shown in the figure. Figure 1 The gas film holes on the high-pressure turbine working blades are numerous, small in diameter and complex in spatial distribution, and precise measurement of the gas film holes on the high-pressure turbine working blades is a prerequisite for objective evaluation of the gas film holes on the high-pressure turbine working blades.

[0003] Currently, when measuring the gas film holes on the high-pressure turbine working blades of an aero-engine, repeated measurements are performed using a measurement device, but there is a lack of calibration means for the measurement accuracy of the measurement device, and the accuracy of the measurement of the gas film holes on the high-pressure turbine working blades cannot be guaranteed, so the processing quality of the gas film holes on the high-pressure turbine working 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 piece for calibrating a gas film hole measurement device of a high-pressure turbine working blade 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 piece for calibrating a gas film hole measurement device of a high-pressure turbine working blade is provided, comprising:

[0009] a first base plate having a standard blade basin curved surface thereon, the standard blade basin curved surface having 1st-5th column standard gas film holes thereon;

[0010] a second base plate vertically arranged with the first base plate, having a standard blade back curved surface thereon, the standard blade back curved surface having 6th-10th column standard gas film holes thereon;

[0011] A third substrate is arranged perpendicularly to the first substrate and the second substrate, and has a standard front edge curve surface and 11-15 standard air film holes on the standard front curve surface;

[0012] Each column of standard air film holes has 6 standard air film holes, which are perpendicular to the plane of the substrate;

[0013] The diameters of the standard air film holes in the 1st, 3rd, 5th, 6th, 8th, 10th, 11th, 13th and 15th columns are all 0.3 mm, the upper tolerance is 0.01 mm, the lower tolerance is 0 mm, and the cylindricity is 0.005 mm;

[0014] The diameters of the standard air film holes in the 2nd, 4th, 7th, 9th, 12th and 14th columns are all 0.4 mm, the upper tolerance is 0.01 mm, the lower tolerance is 0 mm, and the cylindricity is 0.005 mm;

[0015] The horizontal spacing of the standard air film holes in the 1st-5th columns, the 6th-10th columns and the 11th-15th columns is all 4.5 mm, and the vertical spacing is all 8 mm.

[0016] Optionally, in the high-pressure turbine working blade air film hole measuring equipment calibration standard piece, the flatness of the first substrate, the second substrate and the third substrate is 0.01 mm, and the perpendicularity between them is 0.01 mm;

[0017] The position degree of each column of standard air film holes relative to the substrate is 0.01 mm.

[0018] Optionally, in the high-pressure turbine working blade air film hole measuring equipment calibration standard piece, the flatness of the first substrate, the second substrate and the third substrate is 0.01 mm, and the perpendicularity between them is 0.01 mm;

[0019] The straight rod connecting rod is threadedly connected to the corner part of the first substrate, the second substrate and the third substrate at one end, and is connected to the measuring equipment turntable at the other end.

[0020] Optionally, in the high-pressure turbine working blade air film hole measuring equipment calibration standard piece, the flatness of the first substrate, the second substrate and the third substrate is 0.01 mm, and the perpendicularity between them is 0.01 mm;

[0021] The first connecting rod is threadedly connected to the corner part of the first substrate, the second substrate and the third substrate at one end;

[0022] The second connecting rod is connected to the measuring equipment turntable at the other end through a single-double ear structure and a screw at one end.

[0023] In another aspect, a high-pressure turbine working blade air film hole measuring equipment calibration standard piece calibration method is provided, which comprises:

[0024] The calibration preparation step places the high-pressure turbine working blade air film hole measuring equipment calibration standard piece on the workbench of the composite coordinate measuring machine, and the third substrate is horizontally upward;

[0025] A reference surface measurement step is adopted to measure the first substrate, the second substrate and the third substrate planes by using a composite coordinate measuring machine probe sensor;

[0026] A measurement coordinate system construction step is adopted to take the second substrate plane normal direction as the X axis, the third substrate plane normal direction as the Y axis, the first substrate plane normal direction as the Z axis, and the intersection of the first substrate, the second substrate and the third substrate planes as the origin to establish a measurement coordinate system;

[0027] A coordinate fitting step is adopted to import the three-dimensional model of the standard piece for calibrating the high-pressure turbine working blade film hole measurement equipment into the composite coordinate measuring machine, and fit the model coordinate system and the measurement coordinate system;

[0028] A digital model guided optical fiber measurement step is adopted to call the composite coordinate measuring machine, compile a measurement program according to the digital model guidance, complete the measurement of each column of standard film holes on the third substrate, adjust the first substrate to be horizontal and upward, complete the measurement of each column of standard film holes on the first substrate, and adjust the second substrate to be horizontal and upward, complete the measurement of each column of standard film holes on the second substrate;

[0029] A calibration correction step is adopted to compare the diameter, cylindricity and position measurement values of each column of standard film holes with the design values, and calculate the correction error. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 is a schematic diagram of the distribution of the high-pressure turbine working blade film holes of the existing aero-engine;

[0031] Figure 2 is a schematic diagram of the standard piece for calibrating the high-pressure turbine working blade film hole measurement equipment provided by the embodiment of the application;

[0032] Figure 3 is a coordinate schematic diagram of the standard piece for calibrating the high-pressure turbine working blade film hole measurement equipment provided by the embodiment of the application;

[0033] Figure 4 is a schematic diagram of the standard piece for calibrating the high-pressure turbine working blade film hole measurement equipment provided by the embodiment of the application with a straight rod connecting rod;

[0034] Figure 5 is a schematic diagram of the standard piece for calibrating the high-pressure turbine working blade film hole measurement equipment provided by the embodiment of the application with a first connecting rod and a second connecting rod;

[0035] Figure 6 is a schematic diagram of a calibration method of the standard piece for calibrating the high-pressure turbine working blade film hole measurement equipment provided by the embodiment of the application;

[0036] Figure 7This is a flowchart of a calibration method for a standard component used in calibrating a high-pressure turbine working blade film hole measuring device, as provided in an embodiment of this application.

[0037] in:

[0038] 1-First substrate; 2-Second substrate; 3-Third substrate; 4-Straight rod; 5-First connecting rod; 6-Second connecting rod; 7-Composite coordinate measuring machine.

[0039] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0040] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0041] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0042] In addition, it needs to be explained that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and similar words used in the description of the present application should be understood broadly, for example, the connection can be fixed connection, or detachable connection, or integrally connected; 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.

[0043] The specific embodiments of the present application will be further described below in conjunction with the accompanying drawings Figures 1 to 7 The specific embodiments of the present application will be further described below in conjunction with the accompanying drawings

[0044] The present application provides a high-pressure turbine working blade gas film hole measuring device calibration standard part, which has simple structure, compact layout, can simulate gas film holes with different diameters, different space angles and different space positions, and can be calibrated by high-precision measuring equipment. After calibration, it can be used to calibrate the gas film hole measuring device, and can meet the calibration of the gas film hole measuring device under various conditions.

[0045] The high-pressure turbine working blade gas film hole measuring device calibration standard part structure is shown in Figure 2 The main body is composed of three mutually perpendicular thin-walled first base plate 1, second base plate 2 and third base plate 3, which are respectively formed with standard blade basin curve, standard blade back curve and standard leading edge curve, simulating the surface of the gas film hole of the high-pressure turbine working blade of the aero-engine.

[0046] The standard blade basin curve, the standard blade back curve and the standard leading edge curve have a total of 15 columns of standard gas film holes, wherein the first to fifth columns of standard gas film holes are located on the standard blade basin curve, the sixth to tenth columns of standard gas film holes are located on the standard blade back curve, and the eleventh to fifteenth columns of standard gas film holes are located on the standard leading edge curve. Each column of standard gas film holes has 6, a total of 90 holes, all the standard gas film holes are through holes, and all the standard gas film holes are perpendicular to the plane of the base plate.

[0047] The diameters of the first, third, fifth, sixth, eighth, tenth, eleventh, thirteenth and fifteenth columns of standard gas 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 second, fourth, seventh, ninth, twelfth and fourteenth columns of standard gas film holes are all 0.4mm, the upper tolerance is 0.01mm, the lower tolerance is 0mm, and the cylindricity is 0.005mm; The horizontal spacing of the first to fifth columns of standard gas film holes, the sixth to tenth columns of standard gas film holes and the eleventh to fifteenth columns of standard gas film holes is 4.5mm, and the longitudinal spacing is 8mm.

[0048] A threaded hole is provided at the corner part of the first base plate 1, the second base plate 2 and the third base plate 3, which is used for connecting with the measuring equipment.

[0049] The first substrate 1, the second substrate 2 and the third substrate 3 constitute the reference setting of the standard part and the coordinate system establishment as shown in the drawing. Figure 3 The first substrate 1, the second substrate 2 and the third substrate 3 are perpendicular to each other to establish the reference, and further establish the coordinate system. The flatness of the three planes is 0.01mm, the perpendicularity between the three planes is 0.01mm, the position degree of the 90 holes relative to the plane is 0.01mm, the axis of the first to fifth column standard gas film holes is perpendicular to the XOY plane, the axis of the sixth to tenth column standard gas film holes is perpendicular to the YOZ plane, and the axis of the eleventh to fifteenth column standard gas film holes is perpendicular to the XOZ plane.

[0050] The high-pressure turbine working blade gas film hole measuring equipment calibration standard part can be used to calibrate the measuring equipment. In order to connect the measuring equipment turntable, two kinds of connecting rod structures are designed.

[0051] The first connecting rod structure is shown in the drawing. Figure 4 The straight rod connecting rod 4 has a diameter of 10mm and a length of 160mm. In application, one end of the straight rod connecting rod 4 is threadedly connected with the three-perpendicular-substrate corner part of the high-pressure turbine working blade gas film hole measuring equipment calibration standard part, and the other end is connected with the measuring equipment turntable.

[0052] The second connecting rod structure is shown in the drawing. Figure 5 The first connecting rod 5 has a diameter of 10mm and a length of 50mm, and the second connecting rod 6 has a diameter of 10mm and a length of 100mm. In application, one end of the first connecting rod 5 is threadedly connected with the three-perpendicular-substrate corner part of the high-pressure turbine working blade gas film hole measuring equipment calibration standard part, and the other end is connected with one end of the second connecting rod 6 through a single-double-ear structure by means of a screw. The other end of the second connecting rod 6 is connected with the measuring equipment turntable. The angle between the first connecting rod 5 and the second connecting rod 6 can be adjusted by a set screw, so as to change the spatial position of the three-perpendicular-substrate, and further realize the simulation of the gas film hole at different spatial positions.

[0053] In order to calibrate the high-pressure turbine working blade gas film hole measuring equipment calibration standard part, the application further provides a calibration method. The measuring equipment is a composite coordinate measuring machine 7, which is equipped with a plurality of contact and non-contact sensors such as an optical fiber measuring sensor, and can be used for detection of small size.

[0054] The high-pressure turbine working blade gas film hole measuring equipment calibration standard part calibration method is shown in the drawing. Figure 7 The calibration method comprises the following steps.

[0055] A calibration preparation step is performed, in which the standard piece for calibrating the high-pressure turbine working blade film hole measuring device is placed on the worktable of the compound coordinate measuring machine 7, and the third base plate 3 is horizontally upward, as shown in FIG. 8. Figure 6

[0056] A reference surface measurement step is performed, in which the planes of the first base plate 1, the second base plate 2 and the third base plate 3 are measured by using the probe sensor of the compound coordinate measuring machine 7.

[0057] A measurement coordinate system construction step is performed, in which the measurement coordinate system is established by taking the normal direction of the plane of the second base plate 2 as the X axis, the normal direction of the plane of the third base plate 3 as the Y axis, the normal direction of the plane of the first base plate 1 as the Z axis, and the intersection of the planes of the first base plate 1, the second base plate 2 and the third base plate 3 as the origin.

[0058] A coordinate fitting step is performed, in which the three-dimensional model of the standard piece for calibrating the high-pressure turbine working blade film hole measuring device is imported into the compound coordinate measuring machine 7, and the model coordinate system and the measurement coordinate system are fitted.

[0059] A digital model guided optical fiber measurement step is performed, in which the compound coordinate measuring machine 7 is called, measurement programs are compiled according to digital model guidance, the measurement of each column of standard film holes on the third base plate 3 is completed, the first base plate 1 is adjusted to be horizontally upward, the measurement of each column of standard film holes on the first base plate 1 is completed, and the second base plate 2 is adjusted to be horizontally upward, and the measurement of each column of standard film holes on the second base plate 2 is completed.

[0060] A calibration correction step is performed, in which the measured values of the diameters, cylindricities and position degrees of each column of standard film holes are compared with the design values, and the correction errors are calculated.

[0061] The calibration method for the standard piece for calibrating the high-pressure turbine working blade film hole measuring device disclosed in the above embodiment has high calibration efficiency and strong operability, can verify the precision and capability of the measuring device for measuring film holes, can ensure that the measuring device is used for subsequent detection of film holes, and does not need to use a calibration device turntable in the calibration process, so that the measurement uncertainty of the calibration result does not include the component caused by the turntable error, thereby having higher traceable values.

[0062] The technical solution of the present application has 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, and the technical solutions after the changes or replacements will fall within the protection scope of the present application.​

Claims

1. A standard for calibrating a high-pressure turbine blade film hole measuring device, characterized by, It comprises: The first substrate (1) has a standard leaf basin curve on it, and the standard leaf basin curve has 1-5 standard air film holes; The second substrate (2) is vertically arranged with the first substrate (1), and has a standard leaf back curve on it, and the standard leaf back curve has 6-10 standard air film holes; The third substrate (3) is vertically arranged with the first substrate (1) and the second substrate (2), and has a standard leading edge curve on it, and the standard leading edge curve has 11-15 standard air film holes; Each column of standard air film holes has 6 standard air film holes, which are perpendicular to the plane of the substrate; The diameters of the standard air film holes in the 1st, 3rd, 5th, 6th, 8th, 10th, 11th, 13th and 15th columns are all 0.3mm, with an upper tolerance of 0.01mm, a lower tolerance of 0mm and a cylindricality of 0.005mm; The diameters of the standard air film holes in the 2nd, 4th, 7th, 9th, 12th and 14th columns are all 0.4mm, with an upper tolerance of 0.01mm, a lower tolerance of 0mm and a cylindricality of 0.005mm; The horizontal spacing of the standard air film holes in the 1st-5th columns, the 6th-10th columns and the 11th-15th columns is all 4.5mm, and the longitudinal spacing is all 8mm; The flatness of the first substrate (1), the second substrate (2) and the third substrate (3) is 0.01mm, and the perpendicularity between them is 0.01mm; The position accuracy of each column of standard air film holes relative to the substrate is 0.01mm.

2. The standard piece for calibrating high-pressure turbine working blade air film hole measuring equipment according to claim 1, further comprising: A straight rod connecting rod (4) is threadedly connected to the corner part of the first substrate (1), the second substrate (2) and the third substrate (3) at one end, and is connected to the measuring equipment turntable at the other end.

3. The standard piece for calibrating high-pressure turbine working blade air film hole measuring equipment according to claim 1, further comprising: A first connecting rod (5) is threadedly connected to the corner part of the first substrate (1), the second substrate (2) and the third substrate (3) at one end; A second connecting rod (6) is connected to the measuring equipment turntable at one end through a single-double ear structure at the other end of the first connecting rod (5) by means of a screw. It comprises: A calibration preparation step, the high-pressure turbine working blade air film hole measuring equipment calibration standard piece is placed on the workbench of the composite coordinate measuring machine (7), and the third substrate (3) is horizontally upward; 4. A calibration method of a standard piece for calibrating a high-pressure turbine blade film hole measuring apparatus according to any one of claims 1 to 3, characterized by, A reference surface measurement step, the flatness of the first substrate (1), the second substrate (2) and the third substrate (3) is measured by using the probe sensor of the composite coordinate measuring machine (7); A measurement coordinate system construction step, the normal direction of the second substrate (2) plane is taken as the X axis, the normal direction of the third substrate (3) plane is taken as the Y axis, and the normal direction of the first substrate (1) plane is taken as the Z axis. The intersection of the first substrate (1), the second substrate (2) and the third substrate (3) planes is taken as the origin to establish the measurement coordinate system; A coordinate fitting step, the three-dimensional model of the high-pressure turbine working blade air film hole measuring equipment calibration standard piece is imported into the composite coordinate measuring machine (7), and the model coordinate system and the measurement coordinate system are fitted. ​ ​ Digital analog guided optical fiber measurement step, calling composite coordinate measuring machine (7), according to digital analog guide, compiling measurement program, completing the measurement of each column standard gas film hole on the third substrate (3), and adjusting the first substrate (1) to be horizontal upward, completing the measurement of each column standard gas film hole on the first substrate (1), adjusting the second substrate (2) to be horizontal upward, completing the measurement of each column standard gas film hole on the second substrate (2); Calibration correction step, comparing the diameter, cylindricity and position of each column standard gas film hole with the design value, and calculating the correction error.

Images