CN115808148A - Digitized detection method for blade waviness of aircraft engine - Google Patents
Digitized detection method for blade waviness of aircraft engine Download PDFInfo
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- CN115808148A CN115808148A CN202211298320.0A CN202211298320A CN115808148A CN 115808148 A CN115808148 A CN 115808148A CN 202211298320 A CN202211298320 A CN 202211298320A CN 115808148 A CN115808148 A CN 115808148A
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Abstract
The invention provides a digital detection method for the blade waviness of an aircraft engine, and solves the problems that the existing blade waviness detection result is greatly influenced by human factors, the waviness control quality fluctuation is large, and the detection efficiency is low. The waviness detection method changes the measurement mode of the waviness, achieves digital display of the waviness of the blade, and reduces the influence of personnel factors and dependence on personnel experience compared with manual judgment by means of a three-dimensional scanning technology, so that the waviness control quality is more stable.
Description
Technical Field
The invention belongs to the technical field of maintenance of aero-engines, and particularly relates to a digital detection method for the waviness of an aero-engine blade.
Background
Surface waviness refers to the geometric unevenness of an object surface at a distance greater than the surface roughness but less than the surface geometry, and is a geometric error between microscopic and macroscopic. Currently, the waviness of the surface can be detected by a waviness detector, and the corresponding result is obtained mainly by detecting the deviation of the surface relative to the mirror surface reference.
The blade waviness refers to the surface waviness existing in the engine blade, and the waviness of the blade is generally strip-shaped and sheet-shaped. The blade is a space profile, and the surface of the blade can be regarded as being formed by constructing curved surfaces with different curvatures, so that the conventional surface waviness detection method cannot be used for detecting the waviness of the blade.
In the prior production, the blade waviness is compared and checked by using a waviness standard sample, and the method mainly depends on the tactile experience of people for judgment, so that the waviness check is greatly influenced by human factors, so that the waviness control quality fluctuation is large, and the detection efficiency is low. The control of the waviness directly affects the aerodynamic performance of the engine blades, and seriously affects the efficiency of the engine and even causes surge faults. Therefore, a method capable of accurately detecting the blade waviness is required.
Disclosure of Invention
The invention aims to solve the problems that the existing blade waviness detection result is greatly influenced by human factors, the waviness control quality fluctuation is large, and the detection efficiency is low, and provides a digital detection method for the waviness of an aircraft engine blade.
In order to achieve the purpose, the technical solution provided by the invention is as follows:
the digital detection method for the blade waviness of the aircraft engine is characterized by comprising the following steps:
1) Establishing a blade standard profile model according to a design pattern of a blade to be detected through modeling software, and not considering blade profile tolerance during modeling; if tolerance is considered when the standard profile model of the blade is established, an infinite number of models (which are respectively positioned between the minimum model and the maximum model) can be established, so that in order to make the detection means simpler and more convenient, a model without tolerance is established, and as for the tolerance, the tolerance is comprehensively considered when the waviness acceptance standard is determined, so that the detection process is optimized;
2) Guiding the standard profile model of the blade built in the step 1) into a three-dimensional scanning device;
3) Selecting measurement points, and inputting the distribution of the measurement points into three-dimensional scanning equipment;
when selecting the measuring points, determining the measuring points according to the profile change of the blade, the concerned parts and the key parts, namely the measuring point source area basically comes from the parts; such as: firstly, uniformly distributing and selecting measuring points according to the blades, and then adding the measuring points at the air inlet and outlet edges of the blades and the positions with larger curvature change of the profile of the blades, wherein the curvature is positively correlated with the number of the measuring points; in a word, the selection of the measuring points needs to be determined by combining specific blade types and functions, and the selection is determined by a person skilled in the art according to the specific conditions of the blades, and the parts are all generally applicable parts;
4) Placing a blade to be detected in three-dimensional scanning equipment, and scanning the profile of the blade to be detected by using the three-dimensional scanning equipment to obtain an actual profile model of the blade; automatically comparing the deviation between the actual profile of the blade and the standard profile of the blade according to the selected measuring points, and displaying the deviation value on each measuring point; namely, the deviation value of the corresponding point of the actual profile and the standard profile of the blade at each measuring point is automatically displayed.
5) For each measurement point, calculating the difference between the deviation value and the deviation value of the right and/or lower adjacent measurement point of the measurement point (if there are adjacent measurement points on the right and lower sides of the measurement point, the comparison is performed, if there is only right adjacent measurement point or lower adjacent measurement point, the comparison is performed only with the direction having adjacent measurement points, such as: the measurement points located at the right edge or the lower edge), and thus, all the measurement points are calculated, and the maximum value of all the differences is taken as the waviness of the blade to be inspected.
Further, the method also comprises the step 6):
step 3) -step 5) are carried out to the same model standard sample piece that uses when waiting to examine the artifical comparison of blade, measure the waviness of standard sample piece to regard this waviness as waviness control initial value, be used for weighing and wait to examine whether the blade waviness satisfies the operation requirement, be about to examine the waviness of blade and compare (not higher than the waviness control initial value wait to examine the blade and regard as qualified with above-mentioned waviness control initial value).
Further, in order to enable the result of the method of the present invention to be matched with the result of the conventional manual comparison method, in step 6), the self-error of the standard sample piece can be eliminated by correcting the initial value of the waviness control, and the corrected initial value of the waviness control is used as an acceptance standard for the waviness of the blade to be detected. The specific correction mode is as follows:
the method comprises the following steps of respectively checking and accepting a plurality of blades to be detected in the same batch in the following two ways, wherein the first way is to check and accept a standard sample piece through traditional manual comparison, and the second way is to measure the waviness of the blades by the method and compare the waviness with the initial control value of the waviness (the blades to be detected which are not higher than the initial control value of the waviness are regarded as qualified); the acceptance qualification quantity of the two modes is compared, the initial value of the waviness control is corrected, the error of the standard sample piece is eliminated (namely, the manual acceptance result and the ripple detection acceptance result of the equipment are compared, the initial value of the waviness control is corrected, the error caused by the standard sample piece is eliminated, and a person skilled in the art knows how to eliminate the error of the standard sample piece), so that the second mode is matched with the acceptance standard of the first mode, and the manual long-term experience is cured through the method, and the level of the waviness control quality is more stable.
Further, in step 1), UG is used as the modeling software, but other modeling software may be used.
Further, in step 3), the measurement points are increased or decreased according to the curvature change, for example, the curvature is increased, and the measurement points can be increased.
The invention has the advantages that:
1. the method for detecting the waviness changes the measurement mode of the waviness, quantifies the waviness of the blade, and relies on a three-dimensional scanning technology, wherein the three-dimensional scanning detection technology of the blade is that three-dimensional scanning equipment (including contact or non-contact measuring equipment and the like) is used for automatically acquiring the surface point data of the blade through scanning measurement, so that the detection of the geometric dimensions such as the profile of the blade is realized, and the shape data such as the profile of the blade can be measured. The three-dimensional scanning detection technology is used for automatically acquiring the cloud data of the surface points of an object through rapid scanning measurement.
2. The invention realizes the digital display of the blade waviness, is beneficial to stably controlling the profile quality of the blade, is convenient to analyze the relationship between the blade waviness and other parameters of the engine, improves the comprehensive performance of the engine and reduces the failure rate.
3. The blade waviness detection method can accurately measure the blade waviness, reduces the influence of personnel factors and the dependence on personnel experience compared with manual judgment, enables the waviness control quality to be more stable, achieves explicit detection of the blade waviness, can visually display the change situation of the waviness of the blade profile, marks the situation of a corresponding area, is beneficial to targeted maintenance of the blade, and is efficient in acceptance check and stable in quality.
4. The detection method provided by the invention can realize accurate measurement and digital display of the blade waviness of the aircraft engine, is beneficial to improving the control effect of the blade waviness of the engine and improving the overall performance of the engine.
5. When the method is used for measuring the waviness, the artificial long-term experience can be cured through the standard sample piece during quality control, so that the level of the waviness control quality is more stable.
Drawings
FIG. 1 is a blade normalization model;
fig. 2 is a full profile inspection of the blade.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
the method for measuring the waviness of the blades of a certain type of engine comprises the following specific steps:
1. and (3) establishing a blade standard profile model according to the design pattern of the engine blade through UG modeling software, wherein the blade profile tolerance is not considered in modeling, and the standard profile model is shown in the figure 1.
2. And (3) importing the standard profile model of the blade built in the step (1) into a three-dimensional scanning device (for example, a blade multi-axis rotation overspeed measuring machine with the model of CORE).
3. Selecting measurement points according to actual requirements (mainly on the profile change, the concerned part and the key part of the blade, selecting the measurement points according to the use characteristic analysis, avoiding air inlet and exhaust edges, and selecting the measurement points in an evenly distributed manner;
4. placing a blade to be measured in non-contact three-dimensional scanning equipment, and scanning the blade profile by using the three-dimensional scanning equipment to obtain an actual profile model of the blade; automatically comparing the deviation between the actual profile of the blade and the standard profile of the blade according to the selected measuring points, and displaying the deviation value on each measuring point; namely, the deviation value of the corresponding point of the actual profile and the standard profile of the blade at each measuring point is automatically displayed, and the reference figure 2 shows the deviation value.
5. For each measurement point, calculating the difference between the deviation value and the deviation value of the adjacent measurement point to the right and/or below (if there are adjacent measurement points to the right and below of the measurement point, the comparison is performed, if there is only the adjacent measurement point to the right or below, only the comparison is performed with the direction of the adjacent measurement point, such as the measurement point located at the right edge or the lower edge), so that all the measurement points are calculated, see table 1:
TABLE 1 blade waviness measurements
Wherein the maximum difference is 0.17mm, namely the corrugation degree of the engine blade of the type.
Before that, the embodiment also adopts the method to measure the waviness of the standard sample piece with the same model of the blade to be detected, takes the waviness as an initial value of the waviness control, and corrects the value to be used as an acceptance standard of the waviness of the blade to be detected. The specific modification mode is as follows:
the method comprises the following steps of respectively checking and accepting a plurality of (more than 10) blades to be detected in the same batch in the following two ways, wherein the first way is to check and accept a standard sample piece through traditional manual comparison, and the second way is to measure the waviness of the blades by the method and compare the waviness with the initial value of waviness control (the blades to be detected which are not higher than the initial value of waviness control are regarded as qualified); the acceptance qualification quantity of the two modes is compared, the initial value of the waviness control is corrected (in the embodiment, 0.25mm is used as an acceptance standard, namely, the acceptance range can be met, and therefore, the 0.17mm can completely meet the requirement), errors caused by the standard sample piece are eliminated, the second mode is matched with the acceptance standard of the first mode, the artificial long-term experience is cured through the method, the level of the waviness control quality is more stable, and the corrected initial value of the waviness control can be widely applied to production.
Therefore, the method for measuring the waviness and controlling the quality is stable and efficient, and the waviness of the blade to be detected can be measured visually through the output chart.
While the invention has been described with reference to specific embodiments, the invention is not limited thereto, and various equivalent modifications or substitutions can be easily made by those skilled in the art within the technical scope of the present disclosure.
Claims (5)
1. A digital detection method for the blade waviness of an aircraft engine is characterized by comprising the following steps:
1) Establishing a blade standard profile model according to a design pattern of a blade to be detected through modeling software, and not considering blade profile tolerance during modeling;
2) Importing the standard profile model of the blade built in the step 1) into three-dimensional scanning equipment;
3) Selecting measurement points, and inputting the distribution of the measurement points into three-dimensional scanning equipment;
when a measuring point is selected, the measuring point is determined according to the profile change of the blade, the concerned part and the key part;
4) Placing a blade to be detected in three-dimensional scanning equipment, and scanning the profile of the blade to be detected by using the three-dimensional scanning equipment to obtain an actual profile model of the blade; automatically comparing the deviation between the actual profile of the blade and the standard profile of the blade according to the selected measuring points, and displaying the deviation value on each measuring point;
5) And calculating the difference between the deviation value of each measuring point and the deviation value of the adjacent measuring point on the right and/or the lower side of the measuring point, so that all measuring points are calculated, and the maximum value of all the difference values is used as the waviness of the blade to be detected.
2. The digital detection method for the blade waviness of the aircraft engine of claim 1, further comprising step 6):
and 3) carrying out steps 3) -5) on standard sample pieces of the same type used in manual comparison of the blades to be detected, measuring the waviness of the standard sample pieces, and taking the waviness as a waviness control initial value for measuring whether the waviness of the blades to be detected meets the use requirement.
3. The digital detection method for the blade waviness of the aircraft engine of claim 2, wherein:
in the step 6), the initial value of the waviness control can be corrected to eliminate the error of the standard sample piece, and the corrected initial value of the waviness control is used as an acceptance standard of the waviness of the blade to be detected.
4. The digital detection method for the blade waviness of the aircraft engine as claimed in any one of claims 1 to 3, wherein:
in the step 1), UG is adopted by the modeling software.
5. The digital detection method for the blade waviness of the aircraft engine of claim 4, wherein:
and 3), increasing or decreasing the measuring points according to the curvature change.
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| CN202211298320.0A CN115808148A (en) | 2022-10-23 | 2022-10-23 | Digitized detection method for blade waviness of aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117824575A (en) * | 2023-12-28 | 2024-04-05 | 中国航空工业集团公司北京长城计量测试技术研究所 | A method and device for evaluating blade chord-wise waviness |
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- 2022-10-23 CN CN202211298320.0A patent/CN115808148A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117824575A (en) * | 2023-12-28 | 2024-04-05 | 中国航空工业集团公司北京长城计量测试技术研究所 | A method and device for evaluating blade chord-wise waviness |
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