CN113983969B - Aeroengine clearance measurement method based on high-energy X-rays - Google Patents
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Abstract
The application relates to the field of aeroengine clearance measurement, in particular to a high-energy X-ray aeroengine clearance measurement method.
Description
Technical Field
The application belongs to the field of aero-engine clearance measurement, and particularly relates to an aero-engine clearance measurement method based on high-energy X rays.
Background
The gap of the rotor and the stator is an important research content of the aeroengine, on one hand, the gap is important to ensure the performance of the engine, and on the other hand, the reasonable gap is significant to avoid abnormal collision and grinding of the rotor and the stator and ensure the flight safety. The clearance change rule of the working state of the engine is mastered, and is a precondition for the research of a clearance design method. At present, gap analysis mainly depends on two means of calculation and sensor measurement, and the measurement method is commonly a discharge probe measurement method, an eddy current measurement method, a capacitance measurement method, an optical fiber measurement method and the like. Sensors are typically mounted on engine components and the gap between rotors is obtained by measuring the distance between the stator and rotor components, the method being mainly applied to tip gap measurements.
The high-energy X-ray digital imaging technology is used as one of advanced nondestructive testing technologies, and has been applied to foreign aeroengine development, such as British RR, american GE, french SNECMA and the like. The technology breaks through the traditional thought, observes and measures the working condition of internal components in any state of the engine under the conditions of not damaging the internal flow field of the engine, not installing a measuring probe, not being limited by the working temperature and the measuring accessibility of the components of the engine, and the like, grasps the real-time working gap of the components in the engine, and provides data support for gap design and improvement.
The disadvantages of the existing measurement methods are:
1. The method is mainly used for analyzing the radial clearance between the rotor and the stator, and is difficult to realize clearance measurement between the rotor and the stator and axial clearance measurement between components. The method is used for measuring adjacent parts, and cannot measure the absolute displacement change of the parts relative to the main reference of the engine. Only the clearance in the operating state can be measured, and clearance data in the stopped state cannot be obtained.
2. Each position is required to be refitted according to the measuring position, and meanwhile, the gaps of a plurality of positions (such as the comb honeycomb sealing position) cannot be measured by the method due to the limitation of the structural form of parts, the limitation of the use environment temperature of a sensor and the like.
3. The original flow field in the engine is damaged by structural modification, and meanwhile, the sensor probe is easy to pollute and the like due to the influence of working environments such as high temperature and high pressure, oil mist and vibration in the engine, and gap analysis result deviation can be caused due to the mutual influence of the engine and the measuring sensor.
4. The sensor is high in cost, easy to wear in the measuring process, high in measuring cost, and extra time cost is added for testing and refitting.
In view of the higher requirements of the large bypass than the engine on safety and economy, accurate measurement and analysis of the rotor-stator, rotor-rotor and stator-stator gaps are needed by a certain means, and reasonable gap design is carried out, so that the engine is further improved in safety and economy.
Disclosure of Invention
The application aims to provide an aeroengine clearance measurement method based on high-energy X-rays, which aims to solve the problem that in the prior art, accurate measurement of axial and radial clearances among various parts is difficult.
The technical scheme of the application is as follows: an aeroengine clearance measurement method based on high-energy X-rays comprises the steps of assembling an aeroengine to be measured into a high-energy X-ray imaging system; adjusting the position of the accelerator subsystem so that the measurement part is positioned at the center of the imaging area; selecting a proper test run program; driving the aeroengine, the accelerator subsystem and the image acquisition subsystem to work; the accelerator subsystem sends X-rays to the measuring position of the engine, and the image acquisition subsystem receives the X-ray imaging and sends an image measuring result to the image processing subsystem; and respectively selecting characteristic points on two different parts of the region to be detected in the image, acquiring coordinates of the characteristic points relative to the axis position of the aeroengine, acquiring the gap change conditions of 2 parts in different states of the engine, and performing data processing on the gap change conditions.
Preferably, the position adjustment method of the accelerator subsystem and the image acquisition subsystem comprises the steps that the accelerator subsystem and the image acquisition subsystem firstly move to a position to be measured; the accelerator subsystem works, and the image acquisition subsystem acquires a measurement image and starts an image measurement result to the image acquisition subsystem; the image acquisition subsystem determines the positions of the characteristic points on the two parts to be measured according to the image detection result, and determines the difference value between the characteristic points and the center of the image; the image acquisition subsystem sends the difference between the characteristic points and the center of the image to the scanning control subsystem, the scanning control subsystem starts a control command to the bearing and moving subsystem, and the bearing and moving subsystem adjusts the positions of the accelerator subsystem and the image acquisition subsystem according to the difference, so that the characteristic points can be imaged at the center position of the image.
Preferably, when the part to be measured exceeds the imaging range, a reference device is arranged on the main reference intermediate case, a reference block capable of moving along the axial direction and the vertical direction is arranged on the reference device, and the reference block can extend into the imaging area.
Preferably, the measuring directions of the feature points are selected from the position right above and the position right below the engine, and the two feature points are selected at clear positions of adjacent boundaries of the two parts.
Preferably, when the feature points are selected, the selected feature points and the part to be detected are ensured to be on the same piece, and the feature points on different parts are kept consistent along the axial position of the engine or within a certain threshold range.
Preferably, the gap variation analysis method between the different parts includes obtaining coordinates (x 1i,y1i) of the first feature point and coordinates (x 2i,y2i) of the second feature point at different moments in the image measurement result; acquiring an axial gap and a radial gap of two feature points at the same moment, and respectively acquiring a group of gap values corresponding to the two feature points at each different moment; taking the coordinate value of the initial moment of data analysis as a reference to obtain the axial and radial clearance variation between two parts; and (5) corresponding the gap variation quantity at different moments with the working rotation speed of the engine to obtain gap variation data and curves of all states.
Preferably, the first feature point and the second feature point have an axial clearance x i＇＝x2i-x1i and a radial clearance y i＇＝y2i-y1i at the same time; the axial clearance variation delta x i＝xi＇-x1 'and the radial clearance variation delta y i＝yi＇-y1' of the first characteristic point and the second characteristic point.
Preferably, the clearance value analysis method of the two parts to be tested is that a cold state assembly clearance x 0、y0 between the two parts is obtained; acquiring an initial gap and a cold state gap difference delta x 0、Δy0 between two parts before test run starting, and then acquiring an axial gap x i and a radial gap y i between the two parts according to the axial and radial gap variation between the two parts; at cold start, Δx 0＝Δy0 =0; for a hot start, Δχ 0、Δy0 is obtained from the gap analysis of the previous run; when yi >0, the radial direction between the two parts represented by the first characteristic point and the second characteristic point is in a clearance state; when y i is less than 0, the radial directions of the two parts represented by the first characteristic point and the second characteristic point are in a collision and grinding state, and y i is the collision and grinding amount; when x i >0, the second feature point is behind the first feature point; when x i <0, the second feature point is moved forward to the front of the first feature point.
Preferably, at the same time, the axial clearance between two parts is x i＝Δxi+x0+Δx0, and the radial clearance is y i＝Δyi+y0+Δy0.
As a specific implementation mode, the high-energy X-ray imaging system comprises an image processing subsystem, a scanning control subsystem, a bearing and motion subsystem, an accelerator subsystem and an image acquisition subsystem; the image processing subsystem, the scanning control subsystem, the bearing subsystem, the motion subsystem, the accelerator subsystem and the image acquisition subsystem comprise the method.
According to the aeroengine clearance measurement method of the high-energy X-ray, the accelerator subsystem is used for emitting the X-ray, the image acquisition subsystem is used for receiving the X-ray and imaging, and the characteristic points in the imaging area are extracted to obtain the coordinates of the characteristic points relative to the axis position of the aeroengine, so that the clearance change and the clearance value between two parts can be accurately calculated, and the conclusion whether collision and abrasion are generated between the two parts can be accurately obtained.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is a schematic diagram of the overall structure of the present application;
FIG. 2 is a schematic overall flow chart of the present application;
FIG. 3 is a diagram showing the imaging effect of the image according to the present application;
FIG. 4 is a view of a feature point selection corresponding to an image of the present application;
FIG. 5 is a diagram of the gap value calculation process of the present application;
FIG. 6 is a graph of gap values for the present application.
1. An image processing subsystem; 2. a scanning control subsystem; 3. a bearing and movement subsystem; 4. an accelerator subsystem; 5. an image acquisition subsystem; 6. a first feature point; 7. and a second feature point.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
An aeroengine clearance measuring method of high-energy X-rays, as shown in figures 1-4, comprises the following steps:
Step S100, assembling the aeroengine to be tested into a high-energy X-ray imaging system;
Step S200, adjusting the position of the accelerator subsystem 4 to enable the measuring part to be positioned at the center of the imaging area, and carrying out calibration of measuring dimensional accuracy again when the gesture and the position between the high-energy X-ray imaging system and the aeroengine change;
step S300, determining a specific test procedure adopted during measurement according to different states of the concerned engine, wherein the specific test procedure comprises steps and stay time of each step so as to obtain gaps and gap change rules of typical parts of the engine under the procedure;
step S400, driving an aeroengine, an accelerator subsystem 4 and an image acquisition subsystem 5 to work;
Step S500, the accelerator subsystem 4 sends out X-rays to an engine measurement position, and the image acquisition subsystem 5 receives the X-ray imaging and sends an image measurement result to the image processing subsystem 1;
and S600, respectively selecting characteristic points on two different parts of the region to be detected in the image, acquiring coordinates of the characteristic points relative to the axis position of the aeroengine, then acquiring the gap change conditions of 2 parts in different states of the engine, and performing data processing on the gap change conditions.
The characteristic points are arranged at the center positions of the images, so that the characteristic points cannot be separated from the image imaging areas when the characteristic points change, the rotation speed, the temperature, the pneumatic load and the like change in real time along with the change of the state of the engine in the working process of the aeroengine to be tested, the internal parts also change along with the change of the state of the engine, the characteristic points on the two parts are respectively selected, when the two parts change, the two characteristic points correspondingly change along with the change, the coordinates of the two characteristic points relative to the axis position are acquired, the images of different times are shot, and the two characteristic points can all obtain the change relative to the axis position at different times due to the fixed axis position of the aeroengine.
Compared with the relative displacement measurement in the prior art, the two characteristic points can acquire the change of the relative axial position, so that the absolute displacement measurement relative to the main engine design reference is realized, the gap change quantity between the two parts can be effectively obtained, the gap value between the two parts can be accurately determined, whether the clamping stagnation occurs between the two parts or not is known, and the change range of the two characteristic points can acquire the positions of the two characteristic points in an image, so that the radial gap measurement, the axial gap measurement and the absolute displacement measurement of the parts between the rotor and the stator and between the rotor and the stator can be realized, and the gap measurement in the working state and the post-parking state of the engine is realized.
After the installation is completed, the positions and angles of the aero-engine, the accelerator subsystem 4 and the image acquisition subsystem 5 are fixed, so that the positions of the main datum of the aero-engine and the corresponding detection area emitted by the X-rays of the accelerator subsystem 4 are determined, the four-corner coordinates of the image received by the image acquisition subsystem 5 are not changed, and the coordinate change of the characteristic points is that the characteristic points move on the main datum of the engine, so that the accurate measurement can be realized.
Preferably, the position adjustment method of the accelerator subsystem 4 and the image acquisition subsystem 5 is as follows:
Step S410, the accelerator subsystem 4 and the image acquisition subsystem 5 firstly move to a position to be detected;
step S420, the accelerator subsystem 4 works, and the image acquisition subsystem 5 acquires a measurement image and starts an image measurement result to the image acquisition subsystem 5;
Step S430, the image acquisition subsystem 5 determines the positions of the characteristic points on the two parts to be measured according to the image detection result, and determines the difference value between the characteristic points and the center of the image;
in step S440, the image acquisition subsystem 5 sends the difference between the feature point and the center of the image to the scan control subsystem 2, the scan control subsystem 2 sends a control command to the bearing and moving subsystem 3, and the bearing and moving subsystem 3 adjusts the positions of the accelerator subsystem 4 and the image acquisition subsystem 5 according to the difference, so that the feature point can be imaged at the center position of the image.
By setting the characteristic points and capturing the characteristic points, the position of the position to be detected in the whole image can be effectively known, and therefore the position to be detected can be effectively moved to the central position of the image imaging.
Preferably, when the part to be measured exceeds the imaging range, a reference device is arranged on the main reference intermediate case, a reference block capable of moving along the axial direction and the vertical direction is arranged on the reference device, and the reference block can extend into the imaging area.
When one part to be measured is positioned in an image imaging area and the other part is not positioned in the image imaging area, fixing the reference device relative to the part not positioned in the image imaging area, extending the reference block into the imaging area through axial or vertical movement, and then fixing the reference block; the displacement variation and the gap of the parts in the imaging area relative to the reference block are compared, and the reference block is fixed with the parts not in the imaging area, so that the absolute displacement of the two parts relative to the main reference of the engine can be accurately obtained, and the displacement and the gap between the two parts can be accurately obtained.
Preferably, the measuring direction of the feature points is preferably selected from the position right above and the position right below the engine, so that the feature points can be positioned more conveniently and accurately to ensure that accurate data are obtained. In order to ensure that the feature points can be accurately captured and reduce errors caused by deformation of two parts, the feature points are firstly selected at adjacent boundary positions close to the two parts and have enough discrimination, as shown in fig. 4, the first feature points 6 are selected at the end parts of the comb structure, the second feature points 7 are selected on a straight line at the boundary of the honeycomb structure, and the selection of the two feature points simultaneously meets the requirements of smaller distance and higher discrimination.
Preferably, when the feature points are selected, the selected feature points and the part to be detected are ensured to be on the same piece, and the feature points on different parts are kept consistent or within a certain threshold range along the axial position of the engine, so that the initial radial positions of the two feature points are in the same or slightly different state, and the position change of the two feature points can be acquired more conveniently for calculation.
As shown in fig. 5 and 6, the method for analyzing the gap variation between different parts is preferably as follows:
step S610, obtaining the coordinates (x 1i,y1i) of the first feature point 6 and the coordinates (x 2i,y2i) of the second feature point 7 at different moments in the image measurement result;
step S620, obtaining an axial gap and a radial gap of two feature points at the same moment, and respectively obtaining a group of gap values corresponding to the two feature points at each different moment;
Step S630, taking the coordinate value of the initial moment of data analysis as a reference, and acquiring the axial and radial gap variation between two parts;
Step S640, the gap variation amounts at different moments are corresponding to the working rotation speed of the engine, and gap variation data and curves of all states are obtained.
The two feature points calculate the gap change between the two parts by the position change relative to the main reference of the engine, and the measurement is accurate.
Taking the change relation of two parts of the comb teeth and the honeycomb structure as an example for explanation, the measurement and analysis between other structural parts are the same as the method, the first characteristic point 6 is taken by the comb teeth according to the rule, and the second characteristic point 7 is taken by the honeycomb structure according to the rule.
The coordinates of the first feature point 6 at different moments are (x 11,y11)(x12,y12)(x13,y13)……(x1n,y1n) respectively, and the coordinates of the second feature point 7 at different moments are (x 21,y21)(x22,y22)(x23,y23)……(x2n,y2n) respectively, wherein (x 11,y11) and (x 21,y21) are at the same moment, and the subsequent coordinates are similar.
The first feature point 6 and the second feature are at the same time with an axial gap x i＇＝x2i-x1i and a radial gap y i＇＝y2i-y1i.
Based on the coordinate value (x 1＇,y1') of the initial moment of data analysis (usually before starting the engine), the variation of the working gap between the comb teeth and the honeycomb at each moment is as follows:
axial gap variation Δx i＝xi＇-x1 ', radial gap variation Δy i＝yi＇-y1'.
And the gap variation amounts at different moments are corresponding to the working rotation speed of the engine, so that gap variation data and curves of various states are obtained, and the real-time variation trend and variation amplitude of gaps among different parts along with the state of the engine are represented.
Preferably, in order to grasp the clearance or rubbing state between parts at different moments and the specific clearance value or rubbing amount, the data are further processed and analyzed, and the specific method is as follows:
step S650, obtaining a cold state assembly gap x 0、y0 between two parts;
Step S660, obtaining an initial gap and a cold state gap difference value Deltax 0、Δy0 between two parts before starting a test run, and obtaining an axial gap x i and a radial gap y i between the two parts according to the axial and radial gap variation between the two parts, wherein the axial gap between the two parts at the same moment is x i＝Δxi+x0+Δx0, and the radial gap between the two parts is y i＝Δyi+y0+Δy0;
Step S670, during cold start, Δx 0＝Δy0 =0; for a hot start, Δ x0、Δy0 is obtained from the gap analysis of the previous run; when y i is more than 0, the radial direction between the two parts represented by the first characteristic point 6 and the second characteristic point 7 is in a clearance state; when y i is less than 0, the radial directions of the two parts represented by the first characteristic point 6 and the second characteristic point 7 are in a collision and grinding state, and y i is the collision and grinding amount; when x i >0, the second feature point 7 is behind the first feature point 6; when x i <0, the second feature point 7 is advanced to the front of the first feature point 6.
The axial gap and the radial gap between the two parts can be accurately calculated by combining the axial gap variation between the two parts and the difference between the cold assembly gap of the part and the initial gap and the cold state gap before the test run starts, so that whether the collision and the abrasion quantity are generated or not is judged according to the calculated value, and the calculation is convenient and accurate.
An example of the analysis of the axial and radial clearances between two parts under a certain working condition is shown in fig. 5 and 6.
As a specific embodiment, the system further comprises a high-energy X-ray imaging system, which comprises an image processing subsystem 1, a scanning control subsystem 2, a bearing and moving subsystem 3, an accelerator subsystem 4 and an image acquisition subsystem 5.
The accelerator subsystem 4 generates an X-ray beam, the X-ray beam penetrates through a detection area of the aeroengine to form a projection image, the image acquisition subsystem 5 acquires the X-ray projection image by using a high-definition digital imaging system and transmits the image to a computer of the image processing subsystem 1, and the acquired digital image is analyzed and measured by using image checking software; the bearing and moving subsystem 3 bears equipment such as an accelerator and an imaging device, and completes various mechanical movements in a detection process, the scanning control subsystem 2 is used for sending control instructions to the bearing and moving subsystem, the accelerator subsystem 4 and the image acquisition subsystem 5 to control the beam output of the accelerator, the acquisition of the imaging device, the starting and stopping of the bearing and moving device, and the image processing subsystem 1 is responsible for the operation control of the whole system and processes, analyzes and measures the obtained images to obtain a detection conclusion.
The image processing subsystem 1, the scanning control subsystem 2, the bearing and moving subsystem 3, the accelerator subsystem 4 and the image acquisition subsystem 5 comprise the method, and the clearance value between two parts to be measured can be accurately measured by taking the main reference of the aeroengine as the reference.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A high-energy X-ray aeroengine clearance measurement method is characterized in that: comprising the steps of (a) a step of,
Assembling an aeroengine to be tested into a high-energy X-ray imaging system;
adjusting the position of the accelerator subsystem (4) so that the measurement site is located at the center of the imaging region;
selecting a proper test run program;
Driving an aeroengine, an accelerator subsystem (4) and an image acquisition subsystem (5) to work;
The accelerator subsystem (4) emits X rays to an engine measurement position, and the image acquisition subsystem (5) receives X ray imaging and sends an image measurement result to the image processing subsystem (1);
and respectively selecting characteristic points on two different parts of the region to be detected in the image, acquiring coordinates of the characteristic points relative to the axis position of the aeroengine, acquiring the gap change conditions of 2 parts in different states of the engine, and performing data processing on the gap change conditions.
2. The high energy X-ray aircraft engine clearance measurement method of claim 1, wherein: the position adjustment method of the accelerator subsystem (4) and the image acquisition subsystem (5) comprises the following steps of,
The accelerator subsystem (4) and the image acquisition subsystem (5) firstly move to a position to be detected;
the accelerator subsystem (4) works, and the image acquisition subsystem (5) acquires a measurement image and starts an image measurement result to the image acquisition subsystem (5);
The image acquisition subsystem (5) determines the positions of characteristic points on two parts to be measured according to an image detection result, and determines the difference value between the characteristic points and the center of an image;
the image acquisition subsystem (5) sends the difference between the characteristic points and the image center to the scanning control subsystem (2), the scanning control subsystem (2) starts a control command to the bearing and moving subsystem (3), and the bearing and moving subsystem (3) adjusts the positions of the accelerator subsystem (4) and the image acquisition subsystem (5) according to the difference, so that the characteristic points can be imaged at the center position of the image.
3. The high energy X-ray aircraft engine clearance measurement method of claim 1, wherein: when the part to be measured exceeds the imaging range, a reference device is arranged on the main reference intermediate case, a reference block capable of moving along the axial direction and the vertical direction is arranged on the reference device, and the reference block can extend into the imaging area.
4. A method of high energy X-ray aircraft engine clearance measurement according to claim 3, wherein: and the measuring azimuth of the characteristic points is selected from the position right above and the position right below the engine, and simultaneously, the two characteristic points are selected at clear positions of adjacent boundaries of the two parts.
5. The high energy X-ray aircraft engine clearance measurement method of claim 1, wherein: when the feature points are selected, the selected feature points and the part to be detected are ensured to be on the same piece, and the feature points on different parts are kept consistent along the axial position of the engine or within a certain threshold range.
6. The high energy X-ray aircraft engine clearance measurement method of claim 1, wherein: the gap variation analysis method between the different parts is that,
Acquiring coordinates (x 1i,y1i) of a first feature point (6) and coordinates (x 2i,y2i) of a second feature point (7) at different moments in an image measurement result;
Acquiring an axial gap and a radial gap of two feature points at the same moment, and respectively acquiring a group of gap values corresponding to the two feature points at each different moment;
taking the coordinate value of the initial moment of data analysis as a reference to obtain the axial and radial clearance variation between two parts;
and (5) corresponding the gap variation quantity at different moments with the working rotation speed of the engine to obtain gap variation data and curves of all states.
7. The high energy X-ray aircraft engine clearance measurement method of claim 6, wherein: the axial clearance x i＇＝x2i-x1i and the radial clearance y i＇＝y2i-y1i of the first feature point (6) and the second feature point at the same moment; the axial clearance change delta x i＝xi＇-x1 'and the radial clearance change delta y i＝yi＇-y1' of the first characteristic point (6) and the second characteristic point (7).
8. The high energy X-ray aircraft engine clearance measurement method of claim 6, wherein: the gap value analysis method of the two parts to be tested comprises the following steps,
Acquiring a cold state assembly gap x 0、y0 between two parts;
Acquiring an initial gap and a cold state gap difference delta x 0、Δy0 between two parts before test run starting, and then acquiring an axial gap x i and a radial gap y i between the two parts according to the axial and radial gap variation between the two parts;
At cold start, Δx 0＝Δy0 =0; for a hot start, Δχ 0、Δy0 is obtained from the gap analysis of the previous run; when y i is more than 0, the radial direction between the two parts represented by the first characteristic point (6) and the second characteristic point (7) is in a clearance state; when y i is less than 0, the radial directions of the two parts represented by the first characteristic point (6) and the second characteristic point (7) are in a collision and grinding state, and y i is the collision and grinding amount; when x i >0, the second feature point (7) is behind the first feature point (6); when x i <0, the second feature point (7) is advanced to the front of the first feature point (6).
9. The high energy X-ray aircraft engine clearance measurement method of claim 8, wherein: the axial clearance between two parts at the same time is x i＝Δxi+x0+Δx0, and the radial clearance is y i＝Δyi+y0+Δy0.
10. A high-energy X-ray imaging system comprises an image processing subsystem (1), a scanning control subsystem (2), a bearing and moving subsystem (3), an accelerator subsystem (4) and an image acquisition subsystem (5); the image processing subsystem (1), the scanning control subsystem (2), the bearing and movement subsystem (3), the accelerator subsystem (4) and the image acquisition subsystem (5) comprise the method according to any one of claims 1 to 9.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106289120A (en) * | 2016-08-11 | 2017-01-04 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aero-engine sigmatron is tested with adjustable measuring basis device |
| CN110411383A (en) * | 2019-07-26 | 2019-11-05 | 中国航发沈阳发动机研究所 | A kind of aero-engine obturages gap measuring method |
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| US5129010A (en) * | 1989-12-15 | 1992-07-07 | Kabushiki Kaisha Toyoto Chuo Kenkyusho | System for measuring shapes and dimensions of gaps and flushnesses on three dimensional surfaces of objects |
| DE102017129221A1 (en) * | 2017-01-23 | 2018-07-26 | Werth Messtechnik Gmbh | Method and device for determining geometric features on workpieces |
| CN113532337B (en) * | 2021-06-25 | 2023-07-07 | 中国航发沈阳发动机研究所 | Method for determining sealing gap of working state of comb honeycomb structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106289120A (en) * | 2016-08-11 | 2017-01-04 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aero-engine sigmatron is tested with adjustable measuring basis device |
| CN110411383A (en) * | 2019-07-26 | 2019-11-05 | 中国航发沈阳发动机研究所 | A kind of aero-engine obturages gap measuring method |
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