Turbine blade standard part and film hole measuring system calibration method

Abstract

The application discloses a turbine blade standard part and a film hole measuring system calibration method. The turbine blade standard part is used for verifying the measurement accuracy of a film hole measuring system or calibrating the film hole measuring system. The turbine blade standard part comprises a blade, a rim plate, a tenon and a plurality of standard balls. The blade is provided with a plurality of film holes. The tenon is used for positioning and clamping a tool of the film hole measuring system. The standard balls are arranged on the blade and / or the rim plate to establish a part coordinate system. The standard balls are located at the edge of the turbine blade standard part. The turbine blade standard part is measured by using the film hole measuring system to be calibrated. The measurement data is compared with nominal geometric characteristic parameters of the turbine blade standard part. The position degree of the film hole, the hole diameter of the film hole, the profile degree and other related parameters of the film hole measuring system can be evaluated and calibrated.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine, and particularly relates to a turbine blade standard part and a film hole measurement system calibration method. BACKGROUND

[0002] The high-pressure turbine is the largest unit body in the aero-engine which bears mechanical load and thermal load, wherein the turbine blade as the core part of the high-pressure turbine unit body is required to have high high-temperature strength, good corrosion resistance, oxidation resistance and excellent fatigue resistance, and the film cooling technology improves the above-mentioned characteristics of the turbine blade. The advanced film hole design can reach a cooling effect of about 500K, which can effectively slow down the creep fatigue and fracture behavior of the blade, and the service life of the blade is increased by 2-4 times.

[0003] The manufacturing processes of the turbine blade film hole mainly include two processes of electric spark hole making and laser hole making. The process stability and reliability of the two processes have a significant influence on the service performance of the turbine blade. The actual film hole deviates from the design position and contour shape due to the manufacturing error of the hole making process, which leads to the cooling effect of the blade being worse than the design. If it leads to the turbine being 10 DEG C higher than the prediction, the service life of the blade will be reduced by about half, which will cause great hidden troubles to the flight safety. Based on this, the film hole measurement system is of great significance for evaluating the manufacturing error of the hole making process. The measurement performance of the film hole measurement system includes repeatability, reproducibility and traceability (accuracy). The repeatability and reproducibility can be verified by measurement system analysis (MSA), and the measurement accuracy evaluation is a big challenge for the film hole measurement system. SUMMARY

[0004] The technical problem to be solved by the present application is to overcome the problem that the measurement accuracy evaluation of the film hole measurement system is difficult to realize in the prior art, and to provide a turbine blade standard part and a film hole measurement system calibration method.

[0005] The present application solves the above technical problems by the following technical scheme:

[0006] A turbine blade standard part, comprising a blade, a rim plate, a tenon and a plurality of standard balls, the blade, the rim plate and the tenon are connected in sequence from top to bottom, the blade is provided with a plurality of film holes, the standard balls are arranged on the blade and / or the rim plate to establish a part coordinate system, and the standard balls are located at the edge of the turbine blade standard part.

[0007] The standard ball is a very precise artificial ball with a known diameter, and the relevant data of the standard ball is stored in the data processor of the measuring system through pre-measurement. The standard ball is arranged at the edge of the turbine blade standard part, which can avoid the shielding of the standard ball to the film hole and will not affect the measurement of the film hole measuring system to the film hole. The tenon is the same as the formal turbine blade, and can be interchanged with the formal blade. Through the structure form, the turbine blade standard part can be used to evaluate and verify the measurement reference of the film hole measuring system, provide support for the film hole measurement standardization, and better guide the development and process control of the film hole processing technology. For example, the part coordinate system of the standard part can be established by using the standard ball through the three-coordinate measuring instrument, and the film hole standard part establishes a reference reference for evaluating the measurement performance of the film hole, which can be used to verify and calibrate the measurement accuracy of other measuring systems.

[0008] Preferably, the position where the standard ball is connected with the blade and / or the rim plate does not coincide with the target point of six-point positioning.

[0009] The workpiece has six degrees of freedom in space, and six target points are usually used to determine the position of the workpiece. In the technical solution, the standard ball and the six target points are independent of each other and do not interfere with each other, which facilitates the conversion between the data of the standard ball and the data of the six target points.

[0010] Preferably, the number of standard balls is at least 3.

[0011] Three ball center points can determine the blade coordinate system, but the shape and size of the blade are different, and in special cases, the setting of 3 or more standard balls can make the geometric position parameters of the turbine blade more accurate, for example, 4 or 5 standard balls can be set.

[0012] Preferably, at least 1 of the standard balls is located at the top of the blade.

[0013] When measuring, the turntable rotates around the vertical axis, and the standard ball located at the top of the blade will not block the film hole. If the size of the blade is large, in order to ensure the comprehensiveness and accuracy of the data, 2 or more standard balls can be arranged at the top of the blade.

[0014] Preferably, at least 2 of the standard balls are located at the edge of the rim plate facing upward.

[0015] As many standard balls as possible are arranged at the convenient measurement position, and if the size of the blade is large, in order to ensure the comprehensiveness and accuracy of the data, 3 or more standard balls can be arranged at the edge of the rim plate facing upward.

[0016] Preferably, the standard ball located at the top of the blade and the standard ball located at the edge of the rim plate surround the blade.

[0017] As many standard balls as possible are arranged around the turbine blade in each direction, so that the measurement data is more comprehensive and accurate.

[0018] A calibration method of a gas film hole measurement system, comprising,

[0019] Step S1: using a standard measurement system, measuring the turbine blade standard part to obtain standard data of the standard ball, standard data of the gas film hole and standard data of the target point;

[0020] Step S2: according to the standard data of the standard ball and the data of the target point, realizing the conversion of the coordinate system of the blade from the data of the target point to the data of the center of the standard ball;

[0021] Step S3: using the gas film hole measurement system to be calibrated to measure the turbine blade standard part to obtain measurement data, and comparing the measurement data with the geometric position parameters of the turbine blade standard part.

[0022] Through the above steps, the coordinate system of the turbine blade standard part and the nominal characteristic parameters of the gas film hole, including the geometric position, direction and hole diameter of the hole, are established, and the measurement reference of the turbine blade standard part with the gas film hole is established, so as to calibrate the measurement system to be calibrated.

[0023] Preferably, the method further comprises step S4: after step S3, according to the comparison result of step S3, calibrating the related parameters of the gas film hole measurement system to be calibrated to minimize the comparison result.

[0024] Preferably, the standard data of the standard ball includes the center coordinates, the ball diameter and the center distance data of the plurality of standard balls, and the standard data of the gas film hole includes the position and direction data, the hole diameter data and the contour data of the gas film hole relative to the coordinate system of the standard ball.

[0025] Preferably, step S4 further comprises: according to the comparison result of step S3, setting compensation or adjusting the related coefficient parameters of the gas film hole measurement system to be calibrated to calibrate the gas film hole measurement system, and measuring the blade to be measured by using the calibrated gas film hole measurement system.

[0026] Preferably, the step S3 further comprises: establishing a local coordinate system for the gas film hole.

[0027] The positive progress effect of the application is that the nominal characteristic geometric parameters of the turbine blade standard part are established by using the standard data of the standard ball, the turbine blade standard part is measured by using the gas film hole measurement system to be calibrated, the measurement data is compared with the geometric characteristic parameters of the turbine blade standard part, and the measurement accuracy of the gas film hole measurement system can be evaluated and calibrated. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of the standard turbine blade component in this embodiment.

[0029] Figure 2 This is a flowchart of the calibration measurement method for the air film pore measurement system in this embodiment. Detailed Implementation

[0030] The present invention will be further illustrated by way of embodiments below, but the present invention is not limited to the scope of the embodiments described herein.

[0031] like Figure 1 As shown, this embodiment provides a standard turbine blade component, including a blade 1, a rim plate 2, a tenon 3, and four standard balls 4. The blade 1, rim plate 2, and tenon 3 are connected sequentially from top to bottom and integrally formed. The blade 1 has multiple longitudinally evenly distributed film cooling holes 5. The tenon 3 includes three tenons and two mortises. The design of the tenon 3 is the same as that of a standard turbine blade, facilitating clamping and ensuring interchangeability with the standard blade. The rim plate 2 is positioned between the blade 1 and the tenon 3. The standard balls 4 are fixed to the blade 1 and the rim plate 2 by welding using connecting rods 41. Simultaneously, the standard balls 4 are positioned as close as possible to the edge of the turbine blade standard component to establish the coordinate system of the turbine blade standard component.

[0032] The standard ball 4 is a very precise artificial ball with a known diameter. The standard ball 4 plays three roles: first, the same standard ball 4 is measured at different angles to obtain multi-angle synthetic point cloud data, to evaluate the deviation of the point cloud and the fitted standard ball, to verify the performance of the rotating table of the measuring system and the geometric position of the axis relative to the coordinate system of the measuring system. Second, the distance between the centers of the standard balls verifies the spatial accuracy of the measuring system. Third, the coordinates of the centers of three or more standard balls establish a measurement reference for the turbine blade standard part with a gas film hole. The relevant data of the standard ball 4 is stored in the data processor of the measuring system through advance measurement. The standard ball 4 is arranged at the edge of the turbine blade standard part, which can avoid the shielding of the standard ball 4 to the gas film hole 5 and will not affect the measurement of the gas film hole 5 by the gas film hole measuring system. The tenon 3 is the same as the formal turbine blade 1 and can be interchanged with the formal blade. Through this structure, the turbine blade standard part can be used to evaluate and verify the measurement reference of the gas film hole measuring system, provide support for the measurement standardization of the gas film hole 5, and better guide the development and process control of the gas film hole processing technology. The number of standard balls 4 can be determined according to the size and structure of the specific blade 1. In the embodiment, four standard balls 4 can make the geometric position parameters of the turbine blade standard part more accurate. Even if one of the standard balls 4 shields the turbine blade 1, at least two other standard balls 4 can be used to establish the geometric position parameters. Of course, in other embodiments, the standard ball 4 can also be fixed on the edge of the blade 1 standard part by gluing or screwing, to achieve the same effect of evaluating and verifying the measurement reference of the gas film hole measuring system.

[0033] As a preferred embodiment, the positions where the standard ball 4 is connected with the blade 1 and the rim plate 2 are not coincided with the target points of the six-point positioning.

[0034] Generally speaking, a workpiece has six degrees of freedom in space, and six target points are usually used to determine the position of the workpiece. In this technical solution, the standard ball 4 and the six target points are independent of each other and do not interfere with each other, which facilitates the conversion between the data of the standard ball 4 and the data of the six target points.

[0035] As a preferred embodiment, one standard ball 4 is fixed on the upward end wall of the blade 1 by the connecting rod 41, and the other three standard balls 4 are fixed on the upward edge of the rim plate 2 by the connecting rod 41. In this embodiment, the rim plates 2 of the turbine blade standard part are located on both sides of the blade 1, one of which is located lower in the vertical direction, and the other of which is located higher in the vertical direction. One standard ball 4 is arranged on the lower rim plate 2, and two standard balls 4 are arranged on the higher rim plate 2.

[0036] As a preferred embodiment, the standard ball 4 located at the top of the blade 1 and the standard ball 4 located at the edge of the rim plate 2 surround the blade 1 from the top and both sides.

[0037] The structure of the embodiment can arrange the standard balls 4 in all directions of the blade 1 as much as possible, so that the measurement data is more comprehensive and accurate.

[0038] As shown in the figure, a calibration measurement method of an air film hole measurement system comprises, Figure 2

[0039] Step S1: using a standard measurement system, measuring the turbine blade standard part to obtain standard data of the standard ball 4, including the data of the ball center coordinates, the ball diameter, and the ball center distance of the four standard balls 4, and the standard data of the air film hole 5, including the data of the position, direction, and hole diameter of the air film hole;

[0040] Step S2: according to the standard data of the standard ball 4 and the data of the target point, realizing the conversion of the coordinate system of the blade from the data of the target point to the data of the ball center of the standard ball;

[0041] Step S3: using the air film hole measurement system to be calibrated to measure the turbine blade standard part to obtain measurement data, and comparing the measurement data with the geometric position parameters of the turbine blade standard part.

[0042] The calibration measurement method first measures the same standard ball 4 at different angles to obtain multi-angle synthesized point cloud data, so as to establish the geometric position parameters of the turbine blade standard part, and then measures the turbine blade standard part by using the air film hole measurement system to be calibrated to obtain measurement data. By comparing the deviation between the standard data and the measurement data, the performance of the rotating table of the air film hole measurement system to be calibrated and the calibration of the axis relative to the geometric position parameters are evaluated. In addition, the standard value of the ball center distance between the multiple standard balls 4 can be compared with the measurement data to verify the spatial accuracy of the air film hole measurement system to be calibrated. The standard data of the ball center coordinates of the multiple standard balls 4 are used to establish the measurement reference of the turbine blade standard part.

[0043] As a preferred embodiment, it further comprises step S4: after step S3, according to the comparison result of step S3, calibrating the related parameters of the air film hole measurement system to be calibrated to minimize the comparison result.

[0044] As a preferred embodiment, step S4 further comprises: according to the comparison result of step S3, setting a compensation coefficient for the air film hole measurement system to be calibrated to calibrate the air film hole measurement system, and using the calibrated air film hole measurement system to measure the blade 1 to be measured.

[0045] By recalibrating the measurement system to be calibrated, the air film hole measurement capability and the spatial measurement accuracy of the measurement system can be improved, the standardization degree of the air film hole measurement is higher, and it is beneficial to the improvement of the air film hole processing technology and process level. ​

[0046] As a preferred embodiment, step S3 further comprises: establishing a local coordinate system for the film hole 5.

[0047] A local coordinate system is created for each film hole 5, since the geometric position parameters of the film hole 5 relative to the turbine blade standard part are known. The verification of the position of the film hole 5 can be converted into the offset of the hole axis position in the local coordinate system of the film hole 5, and at the same time, it is also convenient to convert the measurement results of different film holes into the same coordinate system for comparison and analysis, which is beneficial to the intuitive comparison of the geometric profile shape deviation of the special-shaped hole.

[0048] Although the specific embodiments of the present application are described above, those skilled in the art should understand that this is only an example, and the protection scope of the present application is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present application, and such changes and modifications all fall within the protection scope of the present application.

Claims

1. A turbine blade standard, characterized by It includes blades, rim plates, tenons, and multiple standard balls. The blades, rim plates, and tenons are connected sequentially from top to bottom. The blades are provided with multiple film cooling holes, and the standard balls are located at the edge of the turbine blade standard component. The position where the standard ball connects to the blade and / or the edge plate does not coincide with the target point of the six-point positioning. The number of standard balls is at least 3; Using the standard data of the standard sphere and the standard data of the film cooling hole, the geometric parameters of the nominal characteristics of the turbine blade standard are established. The coordinate system of the blade is transformed from the data of the target point to the data of the center of the standard sphere. The film cooling hole measurement system to be verified is used to measure the turbine blade standard. The measurement data is compared with the geometric characteristic parameters of the turbine blade standard to evaluate and verify the measurement accuracy of the film cooling hole measurement system.

2. The turbine blade standard of claim 1, wherein At least one of the standard balls is located at the top of the blade.

3. The turbine blade standard of claim 1, wherein At least two of the standard balls are located at the upward-facing edge of the rim plate.

4. The turbine blade standard of claim 1, wherein The standard ball located at the top of the blade and the standard ball located at the edge of the rim plate surround the blade.

5. A method of verifying measurements of an air film orifice measurement system, the method comprising: include Step S1: Using a standard measurement system, measure the turbine blade standard as described in any one of claims 1-4 to obtain the standard data of the standard ball and the standard data of the film gas hole, and measure the target point of the six-point positioning to obtain the data of the target point; Step S2: Based on the standard data of the standard sphere and the data of the target point, the coordinate system of the blade is transformed from being created from the data of the target point to being created from the center data of the standard sphere; Step S3: Use the air film aperture measurement system to be verified to measure the turbine blade standard to obtain measurement data, and compare the measurement data with the geometric position parameters of the turbine blade standard.

6. The method of calibrating a gas film orifice measurement system of claim 5, wherein, The calibration and measurement method for the air film pore measurement system also includes: Step S4: After step S3, based on the comparison results of step S3, the relevant parameters of the air film pore measurement system to be verified are calibrated to minimize the comparison results.

7. The method of calibrating a gas film orifice measurement system of claim 5, wherein, The standard data of the standard sphere includes the center coordinates, diameter, and center-to-center distance of multiple standard spheres, and the standard data of the air film aperture includes the position and orientation data, aperture data, and contour data of the air film aperture relative to the standard sphere in a coordinate system.

8. The method of claim 6, wherein the step of calibrating the gas film orifice measurement system further comprises the step of: Step S4 further includes: based on the comparison results of step S3, setting compensation or adjusting the correlation coefficient parameters of the air film pore measurement system to be verified to calibrate the air film pore measurement system, and using the calibrated air film pore measurement system to measure the blade to be tested. ​ 9. The method of calibrating a gas film orifice measurement system of claim 7, wherein, Step S3 further includes: establishing a local coordinate system for the air film pores.

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