Measuring system and measuring method for deformation field of aero-engine rotor part

Abstract

The invention provides an aero-engine rotor piece deformation field measurement system and method, and the system comprises a measured rotor piece, a fluorescence induction device, a counter, and an image processing assembly, and the measured rotor piece is connected to the fluorescence induction device. The fluorescence sensing device is connected to the counter, the counter is connected to the image processing assembly, and the image processing assembly obtains and processes an image of the detected rotor piece. According to the invention, non-contact measurement of the rotor piece under the conditions of high temperature, high pressure and high rotating speed is realized, and extra load or damage to the rotor piece due to measurement needs is avoided; deformation monitoring of any area of the surface of the rotor piece can be realized, and the problem that local positions cannot be measured due to part configuration is solved; the method has the advantage of high precision, and can realize accurate measurement of small deformation.

Description

Technical Field

[0001] The present invention relates to the technical field of deformation measurement of aero-engine rotor components, and particularly to a deformation field measurement system and method for aero-engine rotor components. Background Art

[0002] When the engine is in operation, the rotor component will deform under the action of centrifugal force, temperature field, aerodynamic load, etc. This deformation mainly includes elastic deformation and plastic deformation. To ensure the safe operation of the engine and avoid the risk of rupture of the rotor component due to excessive deformation or rubbing against adjacent parts, a certain clearance needs to be ensured between the rotor component and adjacent parts during engine design. At the same time, it is also necessary to monitor the deformation of the rotor component during operation.

[0003] However, under high-temperature, high-pressure, and high-speed conditions, traditional measurement methods, such as pasting strain gauges on the rotor component, not only have the risk of falling off but also require drilling holes in the parts to arrange test circuits, causing certain damage to the parts.

[0004] Due to the high-temperature, high-pressure, and high-speed working conditions, traditional measurement methods are difficult to achieve real-time deformation monitoring of the engine rotor component during operation, and the deformation of the rotor component is directly related to the overall operation safety of the engine. Therefore, it is extremely important to measure the deformation of the rotor component during operation in real time and accurately.

[0005] In view of this, the inventors of the present application have designed a deformation field measurement method for aero-engine rotor components in order to overcome the above technical problems. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to overcome the defect that traditional measurement methods in the prior art cannot achieve real-time deformation monitoring of the legal and rotor components during operation, and to provide a deformation field measurement system and method for aero-engine rotor components.

[0007] The present invention solves the above technical problems through the following technical solutions:

[0008] A deformation field measurement system for aero-engine rotor components, characterized in that the deformation field measurement system for aero-engine rotor components includes a rotor component to be measured, a fluorescence induction device, a counter, and an image processing component. The rotor component to be measured is connected to the fluorescence induction device, the fluorescence induction device is connected to the counter, the counter is connected to the image processing component, and the image processing component acquires and processes an image of the rotor component to be measured.

[0009] According to an embodiment of the present invention, the image processing component includes a signal excitation device, a rotational speed recording device, a computer image processing system, and a high-speed camera. The counter is connected to the signal excitation device, the signal excitation device is connected to the rotational speed recording device, and the rotational speed recording device is connected to the computer image processing system;

[0010] The signal excitation device is further connected to the high-speed camera. The high-speed camera acquires an image of the rotor part to be measured, and the high-speed camera is connected to the computer image processing system.

[0011] According to an embodiment of the present invention, a number of fluorescent scatter point markers are provided on the rotor part to be measured, and the fluorescence induction device reads the positions of the fluorescent scatter point markers.

[0012] The present invention discloses a method for measuring the deformation field of an aero-engine rotor part. The method is characterized in that the method for measuring the deformation field of the aero-engine rotor part adopts the aero-engine rotor part deformation field measurement system as described above, and it includes the following steps:

[0013] S 1 Mark the measurement area of the rotor part to be measured with fluorescent scatter points;

[0014] S 2 Capture the fluorescent scatter points in the step S 1 by the fluorescence induction device, and use a counter to record the number of captured fluorescent scatter points;

[0015] S 3 Carry out deformation analysis at each rotational speed state by using the image processing component.

[0016] According to an embodiment of the present invention, the step S 3 further includes the following steps:

[0017] S 31 Set the excitation signal of the signal excitation device;

[0018] S 32 After the high-speed camera receives the instruction in the step S 31 , it takes a photo of the fluorescent scatter points in the measurement area and saves it;

[0019] S 33 After the rotational speed recording device receives the instruction in the step S 31 , it records the current rotational speed;

[0020] S 34 Based on the image of the positions of the fluorescent scatter points recorded in the step S 32 and the step S 33The rotational speed information therein is used to carry out deformation analysis under various rotational speed states through a computer image processing system.

[0021] According to an embodiment of the present invention, in the step S 31 Every time the counter in it increases by 50, an excitation instruction is generated and the instruction is synchronously sent to the high-speed camera and the rotational speed recording device.

[0022] The positive and progressive effects of the present invention are as follows:

[0023] The deformation field measurement system and measurement method of the aero-engine rotor component of the present invention have the following many advantages:

[0024] First, non-contact measurement of the rotor component under high temperature, high pressure and high rotational speed conditions is realized, and no additional load or damage will be caused to the rotor component due to measurement requirements.

[0025] Second, deformation monitoring of any area on the surface of the rotor component can be realized, and the problem that local positions cannot be measured due to the part configuration reason will not occur.

[0026] Third, the measurement system and measurement method have the advantage of high precision and can realize precise measurement of small deformations.

[0027] Fourth, according to the real-time deformation measurement results of the rotor component under the operating state, the existing deformation analysis method can be corrected, thereby improving the deformation analysis ability in the engine design stage. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above-mentioned and other features, properties and advantages of the present invention will become more obvious through the following description in conjunction with the drawings and embodiments. In the drawings, the same reference numerals always represent the same features, wherein:

[0029] Figure 1 is a schematic structural diagram of the deformation field measurement system of the aero-engine rotor component of the present invention.

[0030] Figure 2 is a schematic diagram of the rotor fluorescence scatter point marking in the deformation field measurement method of the aero-engine rotor component of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] To make the above-mentioned objects, features and advantages of the present invention more obvious and understandable, the following detailed description of the specific embodiments of the present invention is provided in conjunction with the drawings.

[0032] Embodiments of the present invention will now be described in detail with reference to the drawings. Preferred embodiments of the present invention will now be described in detail, and examples thereof are shown in the drawings. Whenever possible, the same reference numerals will be used throughout the drawings to represent the same or similar parts.

[0033] In addition, although the terms used in the present invention are selected from well-known and commonly used terms, some of the terms mentioned in the specification of the present invention may be selected by the applicant according to his or her judgment, and their detailed meanings are described in the relevant parts of the description herein.

[0034] In addition, it is required to understand the present invention not only by the actual terms used, but also by the meaning implied by each term.

[0035] Figure 1 It is a schematic structural diagram of the deformation field measurement system for the rotor component of the aero-engine of the present invention. Figure 2 It is a schematic diagram of the rotor fluorescence scatter point marking in the deformation field measurement method for the rotor component of the aero-engine of the present invention.

[0036] As Figure 1 As shown, the present invention discloses a deformation field measurement system for aero-engine rotor components, which particularly includes a rotor component to be measured 10, a fluorescence induction device 20, a counter 30, and an image processing component. Among them, the rotor component to be measured 10 is connected to the fluorescence induction device 20, the fluorescence induction device 20 is connected to the counter 30, the counter 30 is connected to the image processing component, and the image processing component acquires and processes the image of the rotor component to be measured 10.

[0037] Preferably, the image processing component includes a signal excitation device 40, a rotational speed recording device 50, a computer image processing system 60, and a high-speed camera 70. The counter 30 is connected to the signal excitation device 40, the signal excitation device 40 is connected to the rotational speed recording device 50, and the rotational speed recording device 50 is connected to the computer image processing system 60. The signal excitation device 40 is also connected to the high-speed camera 70. The high-speed camera 70 acquires the image of the rotor component to be measured 10, and the high-speed camera 70 is connected to the computer image processing system 60.

[0038] A number of fluorescence scatter point marks are arranged on the rotor component to be measured 10, and the fluorescence induction device 20 reads the positions of the fluorescence scatter point marks. As Figure 2 shown, among which the black scatter points are before deformation, and the gray scatter points are after deformation. The fluorescence scatter point marking area and the scatter point arrangement can be changed according to the measurement requirements.

[0039] In the deformation field measurement system for aero-engine rotor components of the present invention, since this measurement system calculates the deformation field by comparing the relative displacements of the fluorescence scatter points before and after deformation, the fluorescence scatter points used for calculating the deformation field can be regularly distributed or change conformally, and there are no special requirements for the configuration of the rotor component to be measured 10, which has the advantage of measuring the deformation field of irregular objects. The fluorescence points used for marking must have sufficient intensity to ensure that the high-speed camera can record and capture in real time. Before deformation measurement, it is necessary to debug and verify the fluorescence intensity and the quality of the captured fluorescence scatter points.

[0040] The fluorescence induction device 20 is used to capture the fluorescence scatter points of the rotor part 10 to be measured, mainly including a fluorescence detector and a pulse device. The working principle of the fluorescence detector is to excite the fluorescence scatter points with ultraviolet light to generate fluorescence. Therefore, the wavelength range it can sense needs to match the luminescent substance of the fluorescence scatter points. Since the fluorescence detector is relatively insensitive to changes in temperature and pressure and can avoid interference from non-fluorescent components, it can maintain stable detection performance. After the fluorescence detector detects a fluorescence signal, it immediately activates the pulse device, which generates a pulse signal and sends it to the counter.

[0041] The counter 30 is used to receive the pulse signal from the fluorescence induction device 20 and count. The initial value is set to 0, and each time a pulse signal is received, the count is incremented by 1.

[0042] The main function of the signal excitation device 40 is to emit an excitation signal to the high-speed camera 70 and the rotational speed recording device 50 according to the number of pulse counts counted by the counter 30 and the set excitation interval (for example, when the counter increases by 50 or 500, an excitation signal is emitted once). This device mainly consists of a pulse signal exciter. When the set excitation instruction is reached, the pulse signal exciter emits a signal to the high-speed camera 70 and the rotational speed recording device 50. After receiving the excitation instruction, the high-speed camera 70 takes a photo record of the fluorescence scatter points of the rotor part 10 to be measured. At the same time, the rotational speed recording device 50 synchronously records the actual rotational speed at this time.

[0043] The high-speed camera 70 is used to record the real-time displacement of the fluorescence scatter points of the rotor part 10 to be measured. Therefore, its exposure time needs to be calibrated according to the rotational speed of the rotor part to ensure that the actual deformation at the required rotational speed can be captured.

[0044] The rotational speed recording device 50 is used to record the real-time rotational speed. This device can synchronously record with the rotational speed measuring instrument in the test equipment, or perform real-time rotational speed measurement and recording after receiving the rotational speed recording signal from the signal excitation device 40, or synchronize with the counter.

[0045] The computer image processing system 60 mainly calculates the real-time deformation of the rotor part 10 to be measured under various rotational speed conditions based on the displacement of the fluorescence scatter points before and after deformation captured by the high-speed camera 70. This image processing system is mainly digital image processing software, which mainly obtains the real-time displacement image of each scatter point by taking the difference between the fluorescence scatter points before and after deformation. To ensure the accuracy of the displacement field calculation, deformation reference points need to be selected before measurement, and the displacement field calculation is carried out on the premise that the deformation reference remains unchanged. The deformation reference point can be the rotation center or the scatter point at the constrained position. The obtained deformation field can also synchronously obtain the strain field after being processed by the formula (deformation and strain formula).

[0046] The present invention also discloses a method for measuring the deformation field of an aero-engine rotor component, which uses the above-mentioned measurement system for the deformation field of an aero-engine rotor component, and includes the following steps:

[0047] Step S 1 , Mark the measurement area of the rotor component to be measured with fluorescent scattered points;

[0048] Step S 2 , Capture the fluorescent scattered points in the above Step S 1 by a fluorescence induction device, and record the number of captured fluorescent scattered points with a counter;

[0049] Step S 3 , Conduct deformation analysis under various rotational speed states by using an image processing component.

[0050] Preferably, the above Step S 3 further includes the following steps:

[0051] Step S 31 , Set the excitation signal of the signal excitation device.

[0052] Among them, every time the counter in the above Step S 31 increases by 50, an excitation instruction is generated and sent to the high-speed camera and the rotational speed recording device synchronously.

[0053] Step S 32 , After receiving the instruction in the above Step S 31 , the high-speed camera takes pictures of the fluorescent scattered points in the measurement area and saves them.

[0054] Step S 33 , After receiving the instruction in the above Step S 31 , the rotational speed recording device records the current rotational speed.

[0055] Step S 34 , Based on the position images of the fluorescent scattered points recorded in the above Step S 32 and the rotational speed information in the above Step S 33 , conduct deformation analysis under various rotational speed states through a computer image processing system.

[0056] Aiming at the problem that it is difficult to monitor the deformation of the rotor component in real time during operation at present, the present invention proposes an automated, non-destructive, non-contact and high-precision measurement system and measurement method. The measurement system and measurement method can not only realize the dynamic deformation monitoring of the engine rotor component under high temperature, high pressure and high rotational speed conditions, but also cause no damage to the measured part, and have the advantages of automation, non-contact and high precision.

[0057] It has the following characteristics:

[0058] 1. Through the measurement system described in the present invention, the real-time deformation of the rotor component can be measured;

[0059] 2. Through the measurement system described in the present invention, the real-time deformation of the rotor component under high-temperature conditions can be measured;

[0060] 3. Through the measurement system described in the present invention, the real-time deformation of the rotor component under high-pressure conditions can be measured;

[0061] 4. Through the measurement system described in the present invention, the real-time deformation of the rotor component under high-speed rotation conditions can be measured;

[0062] 5. Through the measurement system described in the present invention, the real-time deformation field on the surface of the rotor component in the operating state can be measured;

[0063] 6. Through the measurement system described in the present invention, the small deformation on the surface of the rotor component can be measured in real time;

[0064] 7. Through the measurement system described in the present invention, non-contact real-time deformation measurement of the rotor component can be achieved.

[0065] In summary, the deformation field measurement system and measurement method for the rotor component of an aeroengine in the present invention have the following many advantages:

[0066] 1. Non-contact measurement of the rotor component under high-temperature, high-pressure, and high-speed rotation conditions is achieved, and no additional load or damage will be caused to the rotor component due to measurement requirements;

[0067] 2. Deformation monitoring of any area on the surface of the rotor component can be achieved, and the problem that local positions cannot be measured due to the part configuration will not occur;

[0068] 3. The measurement system and measurement method have the advantage of high precision, and precise measurement of small deformation can be achieved;

[0069] 4. According to the real-time deformation measurement results of the rotor component in the operating state, the existing deformation analysis methods can be corrected, thereby improving the deformation analysis ability in the engine design stage.

[0070] For those skilled in the art, the above invention disclosure is only an example and does not constitute a limitation to this application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are proposed in this application, so such modifications, improvements, and corrections still fall within the spirit and scope of the exemplary embodiments of this application.

[0071] Meanwhile, this application uses specific terms to describe the embodiments of this application. For example, "one embodiment", "an embodiment", and / or "some embodiments" mean a certain feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0072] Although the specific implementation manners of the present invention have been described above, those skilled in the art should understand that these are only examples, and the protection scope of the present invention is defined by the appended claims. Without departing from the principles and essence of the present invention, those skilled in the art can make various changes or modifications to these implementation manners, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. An aero-engine rotor component deformation field measurement system, characterized in that, the aero-engine rotor component deformation field measurement system includes a rotor component to be measured, a fluorescence induction device, a counter and an image processing component. The rotor component to be measured is connected to the fluorescence induction device, the fluorescence induction device is connected to the counter, the counter is connected to the image processing component, and the image processing component acquires and processes an image of the rotor component to be measured.

2. The aero-engine rotor component deformation field measurement system according to claim 1, characterized in that, the image processing component includes a signal excitation device, a rotational speed recording device, a computer image processing system and a high-speed camera. The counter is connected to the signal excitation device, the signal excitation device is connected to the rotational speed recording device, and the rotational speed recording device is connected to the computer image processing system; the signal excitation device is further connected to the high-speed camera, the high-speed camera acquires an image of the rotor component to be measured, and the high-speed camera is connected to the computer image processing system.

3. The aero-engine rotor component deformation field measurement system according to claim 1, characterized in that, a number of fluorescence scatter point marks are provided on the rotor component to be measured, and the fluorescence induction device reads the positions of the fluorescence scatter point marks.

4. An aero-engine rotor component deformation field measurement method, characterized in that, the aero-engine rotor component deformation field measurement method uses the aero-engine rotor component deformation field measurement system according to any one of claims 1-3, and includes the following steps: S 1 , mark the measurement area of the rotor under test with fluorescent scatter points; S 2 、Capture the fluorescence scatter points in the step S 1 through a fluorescence sensing device, and record the number of captured fluorescence scatter points with a counter; S 3 Perform deformation analysis at various rotational speeds using an image processing component.

5. The aero-engine rotor component deformation field measurement method according to claim 4, characterized in that, The said step S 3 further includes the following steps: S 31 Set the excitation signal of the signal excitation device; S 32 After the high-speed camera receives the instruction in step S 31 , it takes pictures of the fluorescence scatter points in the measurement area and saves them; S 33 After the rotational speed recording device receives the instruction in step S 31 , it records the current rotational speed immediately. S 34 Based on the fluorescence scatter position image recorded in the step S 32 and the rotational speed information in the step S 33 perform deformation analysis at each rotational speed state through a computer image processing system.

6. The aero-engine rotor component deformation field measurement method according to claim 5, characterized in that, The step S 31 In the step, every time the counter increases by 50, an excitation instruction is generated and sent to the high-speed camera and the rotation speed recording device synchronously.

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