Rotor structure vibration parameter identification method and device

Abstract

This invention relates to the field of rotor structure technology and discloses a method and apparatus for identifying vibration parameters of rotor structures. Based on the mode shape and vibration stress of each mode, this invention determines the target measurement points for all mode-specific strain gauges within the rotor structure. Vibration stress tests are then performed on the target strain gauges according to these target measurement points, allowing the strain gauges to acquire the resonant response of each mode. During the vibration stress test, the original sampling data of the target strain gauges is interpolated to determine the number of samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling moment. This is further used to generate a three-dimensional curve, identifying the excitation octave frequencies, modal frequencies, and mode shape parameters of the rotor structure. Therefore, this invention can improve the accuracy of identifying modal frequencies and mode shape parameters of disc-shaped rotor structures such as gears in aero-engines during rotation.

Description

Technical Field

[0001] This invention relates to the field of rotor structure technology, and specifically to a method and apparatus for identifying vibration parameters of a rotor structure. Background Technology

[0002] The modal frequencies and mode shapes of disc-shaped rotor structures such as gears in aero-engines are crucial for vibration design. By designing the frequencies, resonance between the rotor structure and the excitation frequency can be avoided during operation, preventing structural damage caused by resonance and ensuring stable operation of the rotor structure under various conditions. Aero-engines typically operate over a wide speed range, making it difficult to avoid resonance in all modes across the entire range. Different mode shapes exhibit varying degrees of hazard when resonating; therefore, vibration isolation designs are generally implemented for the most hazardous modes. Thus, the design must consider both frequency and mode shape parameters. The frequencies of disc-shaped rotor structures such as gears may differ significantly between their rotating and static states. To achieve more accurate frequency design, it is necessary to determine the modal frequencies and mode shapes during rotation.

[0003] In related technologies, the modal frequencies of disc-shaped rotor structures such as gears in aero-engines are mainly obtained using the impact test method. This method is simple to use and can simultaneously obtain modal frequencies and mode shape parameters, but it is difficult to implement under rotational conditions. While conventional analysis methods based on vibration stress testing can obtain the frequencies of the disc structure in its resonant state, they struggle to obtain mode shape parameters. Generally, it is necessary to determine the mode shape by comparing the tested frequencies with the simulated frequencies based on modal simulation analysis results. However, there may be a significant error between the simulated frequencies and the actual frequencies, potentially leading to inaccurate mode shapes. Therefore, the above methods cannot accurately analyze the modal frequencies and mode shape parameters of disc-shaped rotor structures such as gears in aero-engines under rotational conditions. Summary of the Invention

[0004] This invention provides a method and apparatus for identifying vibration parameters of rotor structures, in order to solve the problem of being unable to accurately analyze the modal frequencies and mode shape parameters of disc rotor structures such as gears in aero engines under rotating conditions.

[0005] In a first aspect, this embodiment provides a method for identifying vibration parameters of a rotor structure, the method comprising:

[0006] The rotor structure was analyzed using finite element simulation to obtain the mode shape and vibration stress of each mode.

[0007] Based on the mode shape and vibration stress of each mode, the target measurement points for all mode-specific strain gauges are determined in the rotor structure.

[0008] Vibration stress tests are performed on the target strain gauge according to the target measurement points so that the target strain gauge can obtain the resonance response of each mode. During the vibration stress test, the original sampling data of the target strain gauge is interpolated to determine the number of samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling time.

[0009] Based on the frequency octave corresponding to each sampling time, a three-dimensional curve is determined. The three-dimensional curve is constructed by frequency octave, rotational speed, and amplitude.

[0010] Based on the three-dimensional curve, identify the modal frequencies that meet the preset harmonic conditions and the target curve to which the modal frequencies belong;

[0011] Based on the target curve, the mode shape of the rotor structure is identified by combining the excitation frequency harmonics of the rotor structure.

[0012] In some optional implementations, the mode shape types for each mode include: pitch diameter type, pitch circle type, and a combination of pitch diameter and pitch circle types. The rotating structure is analyzed using finite element simulation to obtain the vibration stress of each mode type, including:

[0013] A three-dimensional solid model of the rotor structure is constructed using a three-dimensional model design system;

[0014] The finite element model of a three-dimensional solid model is solved by a finite element analysis system, and the finite element model is divided into pitch diameter type, pitch circle type and pitch diameter and pitch circle composite type in each mode.

[0015] In some alternative implementations, target measurement points for all mode strain gauges are determined within the rotor structure based on the mode shape and vibration stress of each mode, including:

[0016] Based on the mode shape and vibration stress of each mode, a preset direction is selected as the target measurement point for setting up target strain gauges for all modes.

[0017] In some optional implementations, vibration stress testing is performed on the target strain gauge at the target measurement points to obtain the resonant response of each mode, including:

[0018] Preprocess the surface location of the target measurement point;

[0019] Locate the target measurement point;

[0020] The target strain gauge is attached to the target measurement point after positioning by applying adhesive.

[0021] Construct a vibration stress testing system;

[0022] The resonant response of each mode is obtained by slow frequency sweeping according to the maximum excitation sampling frequency.

[0023] In some optional implementations, during the vibration stress test, the raw sampling data of the target strain gauge is interpolated to determine the number of samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling time, including:

[0024] During vibration stress testing, determine the number of rotational samples per revolution when interpolating the rotor structure;

[0025] During the vibration stress test, the original sampling data of the target strain gauge is interpolated according to the number of samples taken per rotation.

[0026] During vibration stress testing, the target sampling data of the interpolation sampling is segmented to obtain multiple segments of sampling data;

[0027] Determine each sampling time corresponding to each segment of sampled data, where each sampling time corresponds to a rotational speed;

[0028] During the vibration stress test, the octave spectrum at each sampling time is obtained by fast Fourier transform.

[0029] In some optional implementations, based on the three-dimensional curve, the modal frequencies that satisfy the preset octave conditions and the target curve to which the modal frequencies belong are identified, including:

[0030] Based on the number of rotational samplings per revolution of the rotor structure, determine the target reversal point of the three-dimensional curve and the first curve to which the target reversal point belongs;

[0031] Based on the frequency relationship between any two points before the three-dimensional curve reverts, determine the second curve to which those two points belong;

[0032] Determine the mirror image of the first curve about the target turnaround point, and use the mirror image as the third curve;

[0033] Merge the third curve and the second curve into a single target curve, and ensure that any two points on the target curve satisfy the frequency doubling relationship between any two points before the three-dimensional curve reverts to its previous state.

[0034] Based on the target rotational speed, the target mode and harmonics corresponding to the target rotational speed, the modal frequencies of the target curve are identified.

[0035] In some alternative implementations, the mode shape of the rotor structure is identified based on the modal frequency and in conjunction with the excitation harmonics of the rotor structure, including:

[0036] From the target curve, determine the frequency region near the excitation harmonic and identify all resonance points within that frequency region;

[0037] The vibration mode of the rotor structure is identified based on the number of resonance points and the number of nodal diameters on the target curve.

[0038] Secondly, this embodiment provides a vibration parameter identification device for a rotor structure, the device comprising:

[0039] The vibration parameter analysis module is used to analyze the rotor structure through finite element simulation analysis to obtain the mode shape and vibration stress of each mode.

[0040] The measurement location determination module is used to determine the target measurement points for all mode strain gauges in the rotor structure based on the mode shape and vibration stress of each mode.

[0041] The vibration stress testing module is used to perform vibration stress testing on the target strain gauge according to the target measurement point, so that the target strain gauge can obtain the resonance response of each mode. During the vibration stress testing process, the original sampling data of the target strain gauge is interpolated to determine the number of rotation samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling time.

[0042] The three-dimensional curve determination module is used to determine the three-dimensional curve based on the frequency octave corresponding to each sampling time. The three-dimensional curve is constructed by frequency octave, rotational speed, and amplitude.

[0043] The modal frequency identification module is used to identify the modal frequencies that meet the preset harmonic conditions and the target curve to which the modal frequencies belong, based on the three-dimensional curve.

[0044] The mode shape parameter identification module is used to identify the mode shape of the rotor structure based on the target curve and the excitation frequency harmonic of the rotor structure.

[0045] Thirdly, the present invention provides an electronic device, comprising: a memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the computer instructions to perform the vibration parameter identification method for the rotor structure described in the first aspect or any corresponding embodiment.

[0046] Fourthly, the present invention provides a computer-readable storage medium storing computer instructions for causing a computer to execute the vibration parameter identification method for a rotor structure according to the first aspect or any corresponding embodiment described above.

[0047] The technical solution of this invention has the following advantages:

[0048] This invention discloses a method and apparatus for identifying vibration parameters of a rotor structure. Based on the mode shape and vibration stress of each mode, this invention determines target measurement points for all mode-specific strain gauges within the rotor structure. Vibration stress tests are then performed on the target strain gauges according to these target measurement points, allowing the strain gauges to acquire the resonant response of each mode. During the vibration stress test, the original sampling data of the target strain gauges is interpolated to determine the number of samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling moment. This is further used to generate a three-dimensional curve, identifying the excitation octave frequencies, modal frequencies, and mode shape parameters of the rotor structure. Therefore, this invention can improve the accuracy of identifying modal frequencies and mode shape parameters of disc-shaped rotor structures such as gears in aero-engines during rotation. Attached Figure Description

[0049] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0050] Figure 1 This is a schematic flowchart of a vibration parameter identification method for a rotor structure according to an embodiment of the present invention;

[0051] Figure 2 This is a schematic diagram of the target measurement points for different types of target strain gauges according to embodiments of the present invention;

[0052] Figure 3 This is a schematic diagram of the segmentation of interpolated sampling data according to an embodiment of the present invention;

[0053] Figure 4 This is a schematic diagram of modal frequency identification according to an embodiment of the present invention;

[0054] Figure 5 This is a schematic diagram of modal mode identification according to an embodiment of the present invention;

[0055] Figure 6 This is a structural block diagram of a vibration parameter identification device for a rotor structure according to an embodiment of the present invention;

[0056] Figure 7 This is a schematic diagram of the hardware structure of an electronic device according to an embodiment of the present invention. Detailed Implementation

[0057] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0058] It is understood that before using the technical solutions disclosed in the various embodiments of the present invention, users should be informed of the types, scope of use, and usage scenarios of the personal information involved in the present invention and their authorization should be obtained in accordance with relevant laws and regulations through appropriate means.

[0059] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0060] According to an embodiment of the present invention, a method for identifying vibration parameters of a rotor structure is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0061] This embodiment provides a method for identifying vibration parameters of a rotor structure, which can be used in computer equipment or mobile terminals, such as desktop computers, laptops, servers, mobile phones, tablets, etc. Figure 1 This is a flowchart of a vibration parameter identification method for a rotor structure according to an embodiment of the present invention, such as... Figure 1 As shown, the process includes the following steps:

[0062] Step S101: Analyze the rotor structure using finite element simulation to obtain the mode shape and vibration stress of each mode.

[0063] Specifically, finite element simulation analysis is a method of analysis performed using a finite element simulation analysis system, which includes, but is not limited to, software systems such as ANSYS and Abaqus. Rotor structures include, but are not limited to, disc-shaped rotor structures such as gears and impellers in aero-engines.

[0064] In a specific example, the mode types for each mode order include: pitch diameter mode, pitch circle mode, and a combination of pitch diameter and pitch circle mode.

[0065] Specifically, a nodal-diameter mode refers to a diameter line with zero displacement in the mode shape, and the vibration mode of a nodal-diameter mode is defined by the nodal diameter. For disk-like structures, the main strain in a nodal-diameter mode is generated by bending along the circumference. A nodal-circle mode refers to a concentric ring with zero displacement in the mode shape, and the main strain in a nodal-circle mode is generated by bending along the radius. A combined nodal-diameter and nodal-circle mode, which contains both nodal diameter and nodal circle, has a more complex vibration mode. Figure 2 The diagram shows the mode shape type for each mode.

[0066] In some specific implementations, step S101 above analyzes the rotating structure using finite element simulation to obtain the vibration stress of each mode, including:

[0067] Step a1: Construct a three-dimensional solid model of the rotor structure using a three-dimensional model design system.

[0068] Step a2: Solve the finite element model of the three-dimensional solid model in each mode using a finite element analysis system to determine the pitch diameter type, pitch circle type, and pitch diameter and pitch circle composite type.

[0069] For example, in a finite element analysis system, the element type, element size, and number of elements are set for the entire or local area of ​​the rotor, thereby automatically generating the mesh. Then, based on the design drawings of the 3D solid model, the boundary conditions of the finite element model are set, for example, constraining the displacement of all nodes on the mating surface of the rotor structure's main shaft. Finally, the direct method or iterative method is set to extract the mode shape and vibration stress for each mode.

[0070] This embodiment uses a finite element analysis system to perform modal simulation analysis on the rotor structure. The simulation analysis requires the application of boundary conditions based on the actual constraints. The analyzed modes include all pitch diameter, pitch circle, and combined pitch diameter and pitch circle modes within the excitation frequency range, thereby obtaining the mode shape and vibration stress for each mode.

[0071] Step S102: Based on the mode shape and vibration stress of each mode, determine the target measurement points for all mode-specific strain gauges in the rotor structure.

[0072] Specifically, the target measurement point is the measurement location where the target strain gauge is attached. The target strain gauge is a stress detection device for detecting rotor structure.

[0073] In some specific embodiments, step S102 above involves determining the target measurement points for all mode strain gauges in the rotor structure based on the mode shape and vibration stress of each mode, including:

[0074] Based on the mode shape and vibration stress of each mode, a preset direction is selected as the target measurement point for setting up target strain gauges for all modes.

[0075] In a specific example, when the mode shape of each mode is the pitch-radius type, the circumferential direction of the rotor structure is selected as the preset direction, and the target measurement points of the target strain gauges under all modes are set in combination with the vibration stress.

[0076] For example, when the mode shape of each mode is a pitch-diameter type, after selecting the circumferential direction of the rotor structure as the preset direction, the vibration stress with the largest vibration stress in each mode is selected as the target measurement point of the target strain gauge under all modes. Figure 2 In the case of the circumferential type, the target measurement point is determined by the circumferential direction.

[0077] In another specific example, when the mode shape of each mode is a pitch circle, the radial direction of the rotor structure is selected as the preset direction, and the target measurement points of the target strain gauges under all modes are set in combination with the vibration stress.

[0078] For example, when the mode shape of each mode is a pitch circle, after selecting the radial direction of the rotor structure as the preset direction, the vibration stress with the largest vibration stress is selected as the target measurement point of the target strain gauge under all modes based on the vibration stress of each mode. Figure 2 In this context, the nodal circle is used to determine the target measurement point in the radial direction.

[0079] In another specific example, when the mode shape of each mode is a combination of pitch diameter and pitch circle, the rotor structure is selected along the radial 45-degree direction as the preset direction, and the target measurement points of the target strain gauges under all modes are arranged in combination with the vibration stress.

[0080] For example, when the mode shape of each mode is a combination of pitch diameter and pitch circle, the rotor structure is selected along a radial direction of 45 degrees as the preset direction. Based on the vibration stress of each mode, the vibration stress with the highest vibration stress is selected as the target measurement point for the target strain gauge under all modes. Figure 2 In the case of the combined pitch diameter and pitch circle type, the target measurement point is determined along the radial direction at 45 degrees.

[0081] In some alternative implementations, when actually determining the target measurement point of the target strain gauge, in addition to considering the mode shape and vibration stress of each mode, it is also necessary to consider the process that can be realized on the rotor structure as the target measurement point.

[0082] Specifically, after obtaining the vibration stress of each mode, target measurement points with larger vibration stress and feasible process are selected for patching. The same strain gauge should cover as many modes as possible, and different modes should have corresponding target measurement points.

[0083] Step S103: Perform vibration stress test on the target strain gauge according to the target measurement point so that the target strain gauge can obtain the resonance response of each mode. During the vibration stress test, interpolate the original sampling data of the target strain gauge to determine the number of rotation samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling time.

[0084] In some specific embodiments, step S103 above, which involves performing vibration stress testing on the target strain gauge according to the target measurement point, so that the target strain gauge obtains the resonant response of each mode, includes:

[0085] Step b1: Preprocess the surface location of the target measurement point.

[0086] The surface location of the target measurement point is cleaned and pretreated.

[0087] Step b2: Locate the target measurement point.

[0088] Specifically, use a positioning template or high-precision calipers to precisely position the target measurement point according to the calculated parameters. Ensure that the direction of the grid wires of the target strain gauge is completely consistent with the direction of the principal stress to be measured.

[0089] Step b3: Apply adhesive to attach the target strain gauge to the positioned target measurement point.

[0090] Specifically, a thin layer of adhesive can be uniformly coated onto the target strain gauge substrate using adhesives such as cyanoacrylate quick-drying adhesive or epoxy resin adhesive.

[0091] Step b4: Construct a vibration stress testing system for vibration stress testing.

[0092] Specifically, after the target strain gauge is successfully attached, a vibration stress testing system can be constructed using a suitable dynamic strain gauge and with the correct bridge circuit settings.

[0093] Step b5: Obtain the resonant response of each mode by slow frequency sweeping according to the maximum excitation sampling frequency.

[0094] For example, the target strain gauge is attached according to the target measurement point of the positioned target strain gauge, and a vibration stress test is performed. The strain sampling frequency needs to be high enough, so this embodiment sets the maximum excitation sampling frequency, specifically at a sampling frequency more than 2.5 times the maximum excitation frequency, and obtains the resonant response of each mode by a slow frequency sweep method.

[0095] In some specific implementations, step S103 above, during the vibration stress test, involves interpolating the original sampling data of the target strain gauge to determine the number of samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling time, including:

[0096] Step c1: During the vibration stress test, determine the number of rotational samples per revolution when interpolating the rotor structure.

[0097] Step c2: During the vibration stress test, interpolate the original sampling data of the target strain gauge according to the number of sampling cycles per week.

[0098] Specifically, during vibration stress testing, the target strain gauge is sampled at equal time intervals, with the time interval between adjacent sampling points being equal. However, when the rotor structure's rotational speed changes, the number of sampling points per revolution varies. Therefore, it is necessary to re-interpolate the original sampling data to ensure that the target strain gauge has the same number of sampling points per revolution. The number of sampling points per revolution after the rotor structure is re-sampled is denoted as... .

[0099] Step c3: During the vibration stress test, the target sampling data of the interpolation sampling is segmented to obtain multiple segments of sampling data.

[0100] Step c4: Determine each sampling time corresponding to each segment of sampled data, where each sampling time corresponds to a rotational speed.

[0101] Step c5: During the vibration stress test, the octave spectrum at each sampling time is obtained by fast Fourier transform.

[0102] The target sampled data for re-interpolation is segmented, specifically, as follows: Figure 3 The diagram shows a segmentation of the interpolated sampling data. Each segment of the target sampling data has the same length, and overlap between adjacent data is allowed. The time corresponding to the center point of the i-th segment of the target sampling data is... A Fast Fourier Transform is performed on each segment of target sampled data to obtain the octave spectrum at each time step. Based on each time step... Rotor speed corresponding to the target sampling data During vibration stress testing, the octave spectrum at each sampling moment is obtained through Fast Fourier Transform, which allows us to obtain the octave spectrum at different rotational speeds.

[0103] Step S104: Determine the three-dimensional curve based on the frequency octave corresponding to each sampling time. The three-dimensional curve is constructed by frequency octave, rotational speed and amplitude.

[0104] Specifically, based on the octave spectrum corresponding to each sampling moment, the logarithm of the amplitude at each sampling moment is taken, thereby obtaining a three-dimensional curve constructed by the octave, rotational speed, and amplitude.

[0105] Step S105: Based on the three-dimensional curve, identify the modal frequencies that satisfy the preset harmonic conditions and the target curve to which the modal frequencies belong.

[0106] In some specific implementations, step S105 above, which identifies the modal frequencies that satisfy the preset harmonic conditions based on the three-dimensional curve, includes:

[0107] Step d1: Based on the number of rotational samplings per week of the rotor structure, determine the target reversal point of the three-dimensional curve and the first curve to which the target reversal point belongs.

[0108] Specifically, since the modal frequency is a continuously changing curve, the maximum value of the horizontal axis (dominant frequency) of the curve is half the number of samples per revolution of the rotor structure, that is... 3D curves in The curve will bounce back at this point, causing the three-dimensional curve to... The point where the curve reverts is considered the target revert point, and the curve corresponding to the target revert point is considered the first curve, which is also the revert curve.

[0109] Step d2: Based on the frequency relationship between any two points before the three-dimensional curve reverts, determine the second curve to which those two points belong.

[0110] Specifically, the frequency harmonics of the three-dimensional curve at any two points before the curve wraps back. , and rotational speed , The following relationship must be satisfied: .

[0111] Step d3: Determine the mirror image of the first curve about the target turnaround point, and use the mirror image as the third curve.

[0112] Step d4: Merge the third curve and the second curve into the same target curve, and make any two points on the target curve satisfy the frequency doubling relationship between any two points before the three-dimensional curve folds back.

[0113] Specifically, specifically as Figure 4 The diagram shown is a schematic diagram of modal frequency identification. Figure 4 In the middle, the return curve about the target return point The mirror curve and the second curve before the foldback form a continuous smooth curve, and the mirror curve satisfies the harmonic relationship between any two points before the foldback of the three-dimensional curve, that is, it satisfies the above formula. Requirements.

[0114] Step d5: Identify the modal frequencies of the target curve based on the target rotational speed, the target mode corresponding to the target rotational speed, and the harmonics.

[0115] Specifically, the modal frequencies of the target curve are identified using the following formula.

[0116]

[0117] in, The modal frequency of the target curve, in Hertz. The frequency multiplier corresponding to the target rotational speed. The target rotational speed is expressed in revolutions per minute (rpm).

[0118] Step S106: Based on the target curve, identify the mode shape of the rotor structure by combining the excitation frequency of the rotor structure.

[0119] Specifically, based on the target curve obtained in the above manner, combined with the excitation frequency of the rotor structure... (For gears, the excitation frequency is the meshing frequency), and modal vibration mode identification is performed.

[0120] In some specific implementations, step S106 above, which identifies the mode shape of the rotor structure based on the target curve and in conjunction with the excitation harmonic of the rotor structure, includes:

[0121] Step e1: Determine the frequency region near the excitation harmonic from the target curve, and identify all resonance points within that frequency region.

[0122] Step e2: Identify the mode shape of the rotor structure based on the number of resonance points and the number of nodal diameters on the target curve.

[0123] In a specific example, step e2 above, which identifies the mode shape of the rotor structure based on the number of resonance points and the number of nodal diameters on the target curve, includes:

[0124] When the number of resonance points near the target point on the target curve corresponding to the excitation frequency is 1, the vibration mode of the target mode corresponding to the target point of the rotor structure is determined to be the pitch circle vibration mode.

[0125] In a specific example, step e2 above, which identifies the mode shape of the rotor structure based on the number of resonance points and the number of nodal diameters on the target curve, includes:

[0126] When the number of resonance points near the target point on the target curve corresponding to the excitation frequency is 2, the mode shape of the target mode of the rotor structure at the target point is identified as the pitch diameter mode shape based on the frequency corresponding to each resonance point. The frequency corresponding to each resonance point is calculated based on the pitch diameter.

[0127] For example, frequency multiplication. There are two resonance points on the nearby target curve, and the octaves corresponding to the two resonance points are... and When the target point's mode shape is m, then the mode shape of that order is a nodal-radius mode shape, and the corresponding nodal number is m.

[0128] In a specific example, step e2 above, which identifies the mode shape of the rotor structure based on the number of resonance points and the number of nodal diameters on the target curve, includes:

[0129] When the number of resonance points near the target point on the target curve corresponding to the excitation frequency is 3, based on the excitation frequency corresponding to the target point and the frequency corresponding to each resonance point, the mode shape of the rotor structure at the target point is identified as a composite mode of pitch diameter and pitch circle. The frequency corresponding to each resonance point is calculated based on the pitch diameter.

[0130] For example, such as Figure 5 As shown, excitation frequency multiplication There are three resonance points on the nearby target curve, and the octaves corresponding to the three resonance points are respectively... , , At that time, the mode shape of the rotor structure at the target point is a composite mode of pitch diameter and pitch circle, and the corresponding pitch diameter number is m.

[0131] This embodiment also provides a vibration parameter identification device for a rotor structure, which is used to implement the above embodiments and preferred embodiments; details already described will not be repeated. As used below, the term "module" can refer to a combination of software and / or hardware that performs a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0132] This embodiment provides a vibration parameter identification device for a rotor structure, such as... Figure 6 As shown, the device includes:

[0133] The vibration parameter analysis module 601 is used to analyze the rotor structure through finite element simulation analysis to obtain the mode shape and vibration stress of each mode.

[0134] The measurement location determination module 602 is used to determine the target measurement points for all mode-specific strain gauges in the rotor structure based on the mode shape and vibration stress of each mode.

[0135] The vibration stress testing module 603 is used to perform vibration stress testing on the target strain gauge according to the target measurement point, so that the target strain gauge can obtain the resonance response of each mode. During the vibration stress testing process, the original sampling data of the target strain gauge is interpolated to determine the number of rotation samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling time.

[0136] The three-dimensional curve determination module 604 is used to determine the three-dimensional curve based on the frequency octave corresponding to each sampling time. The three-dimensional curve is constructed by frequency octave, rotational speed and amplitude.

[0137] The modal frequency identification module 605 is used to identify the modal frequencies that meet the preset harmonic conditions and the target curve to which the modal frequencies belong, based on the three-dimensional curve.

[0138] The mode shape parameter identification module 606 is used to identify the mode shape of the rotor structure based on the target curve and the excitation frequency harmonic of the rotor structure.

[0139] In some optional implementations, the mode shape types for each mode include: pitch diameter type, pitch circle type, and a combination of pitch diameter and pitch circle type. The vibration parameter analysis module 601 is specifically used for:

[0140] A three-dimensional solid model of the rotor structure is constructed using a three-dimensional model design system;

[0141] The finite element model of a three-dimensional solid model is solved by a finite element analysis system, and the finite element model is divided into pitch diameter type, pitch circle type and pitch diameter and pitch circle composite type in each mode.

[0142] In some alternative implementations, the measurement position determination module 602 is specifically used for:

[0143] Based on the mode shape and vibration stress of each mode, a preset direction is selected as the target measurement point for setting up target strain gauges for all modes.

[0144] In some alternative implementations, the measurement position determination module 602 is further specifically used for:

[0145] Preprocess the surface location of the target measurement point;

[0146] Locate the target measurement point;

[0147] The target strain gauge is attached to the target measurement point after positioning by applying adhesive.

[0148] Construct a vibration stress testing system;

[0149] The resonant response of each mode is obtained by slow frequency sweeping according to the maximum excitation sampling frequency.

[0150] In some alternative implementations, the vibration stress testing module 603 is specifically used for:

[0151] During vibration stress testing, determine the number of rotational samples per revolution when interpolating the rotor structure;

[0152] During the vibration stress test, the original sampling data of the target strain gauge is interpolated according to the number of samples taken per rotation.

[0153] During vibration stress testing, the target sampling data of the interpolation sampling is segmented to obtain multiple segments of sampling data;

[0154] Determine each sampling time corresponding to each segment of sampled data, where each sampling time corresponds to a rotational speed;

[0155] During the vibration stress test, the octave spectrum at each sampling time is obtained by fast Fourier transform.

[0156] In some alternative implementations, the modal frequency identification module 605 is specifically used for:

[0157] Based on the number of rotational samplings per revolution of the rotor structure, determine the target reversal point of the three-dimensional curve and the first curve to which the target reversal point belongs;

[0158] Based on the frequency relationship between any two points before the three-dimensional curve reverts, determine the second curve to which those two points belong;

[0159] Determine the mirror image of the first curve about the target turnaround point, and use the mirror image as the third curve;

[0160] Merge the third curve and the second curve into a single target curve, and ensure that any two points on the target curve satisfy the frequency doubling relationship between any two points before the three-dimensional curve reverts to its previous state.

[0161] Based on the target rotational speed, the target mode and harmonics corresponding to the target rotational speed, the modal frequencies of the target curve are identified.

[0162] In some alternative implementations, the mode shape parameter identification module 606 is specifically used for:

[0163] From the target curve, determine the frequency region near the excitation harmonic and identify all resonance points within that frequency region;

[0164] The vibration mode of the rotor structure is identified based on the number of resonance points and the number of nodal diameters on the target curve.

[0165] The vibration parameter identification device for rotor structures provided in this embodiment of the invention can execute the vibration parameter identification method for rotor structures provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects of the method. Further functional descriptions of the above modules and units are the same as in the corresponding embodiments described above, and will not be repeated here.

[0166] Figure 7 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention.

[0167] The following is a detailed reference. Figure 7 , Figure 7 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention.

[0168] The following is a detailed reference. Figure 7 The diagram illustrates a structural schematic suitable for implementing an electronic device according to embodiments of the present invention. The electronic device may include a processor (e.g., a central processing unit, graphics processor, etc.) 701, which can perform various appropriate actions and processes based on a program stored in a read-only memory (ROM) 702 or a program loaded from memory 708 into random access random access memory (RAM) 703. The RAM 703 also stores various programs and data required for the operation of the electronic device. The processor 701, ROM 702, and RAM 703 are interconnected via a bus 704. An input / output (I / O) interface 705 is also connected to the bus 704.

[0169] Typically, the following devices can be connected to I / O interface 705: input devices 706 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 707 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; memory devices 708 including, for example, magnetic tapes, hard disks, etc.; and communication devices 709. Communication device 709 allows electronic devices to exchange data via wireless or wired communication with other devices. Although Figure 7 Electronic devices with various devices are shown, but it should be understood that it is not required to implement or have all of the devices shown, and more or fewer devices may be implemented or have instead.

[0170] In particular, according to embodiments of the present invention, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of the present invention include a computer program product comprising a computer program carried on a non-transitory computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via a communication device 709, or installed from a memory 708, or installed from a ROM 702. When the computer program is executed by the processor 701, it performs the functions defined in the vibration parameter identification method for rotor structures according to embodiments of the present invention.

[0171] Figure 7 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of use of the embodiments of the present invention.

[0172] This invention also provides a computer-readable storage medium. The methods described above according to embodiments of the invention can be implemented in hardware or firmware, or implemented as computer code that can be recorded on a storage medium, or implemented as computer code downloaded via a network and originally stored on a remote storage medium or a non-transitory machine-readable storage medium and then stored on a local storage medium. Thus, the methods described herein can be processed by software stored on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. The storage medium can be a magnetic disk, optical disk, read-only memory, random access memory, flash memory, hard disk, or solid-state drive, etc.; further, the storage medium can also include combinations of the above types of memory. It is understood that computers, processors, microprocessor controllers, or programmable hardware include storage components capable of storing or receiving software or computer code. When the software or computer code is accessed and executed by the computer, processor, or hardware, the vibration parameter identification method for the rotor structure shown in the above embodiments is implemented.

[0173] A portion of this invention can be applied as a computer program product, such as computer program instructions, which, when executed by a computer, can invoke or provide the methods and / or technical solutions according to the invention through the operation of the computer. Those skilled in the art will understand that the forms in which computer program instructions exist in a computer-readable medium include, but are not limited to, source files, executable files, installation package files, etc. Correspondingly, the ways in which computer program instructions are executed by a computer include, but are not limited to: the computer directly executing the instructions, or the computer compiling the instructions and then executing the corresponding compiled program, or the computer reading and executing the instructions, or the computer reading and installing the instructions and then executing the corresponding installed program. Here, the computer-readable medium can be any available computer-readable storage medium or communication medium accessible to a computer.

[0174] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A method for identifying vibration parameters of a rotor structure, characterized in that, The method includes: The rotor structure was analyzed using finite element simulation to obtain the mode shape and vibration stress of each mode. Based on the mode shape and vibration stress of each mode, the target measurement points for all mode-specific strain gauges are determined in the rotor structure. Vibration stress test is performed on the target strain gauge according to the target measurement point so that the target strain gauge can obtain the resonance response of each mode. During the vibration stress test, the original sampling data of the target strain gauge is interpolated to determine the number of rotation samples per revolution of the rotor structure and the octave spectrum corresponding to each sampling time. A three-dimensional curve is determined based on the frequency doubling frequency corresponding to each sampling time. The three-dimensional curve is constructed by frequency doubling, rotational speed, and amplitude. Based on the three-dimensional curve, identify the modal frequencies that satisfy the preset harmonic conditions and the target curve to which the modal frequencies belong; Based on the target curve, the vibration mode of the rotor structure is identified by combining the excitation frequency harmonics of the rotor structure. Based on the three-dimensional curve, identify the modal frequencies that satisfy the preset harmonic conditions and the target curves to which the modal frequencies belong, including: Based on the number of rotational samplings per week of the rotor structure, determine the target break-back point of the three-dimensional curve and the first curve to which the target break-back point belongs; Based on the frequency relationship between any two points before the three-dimensional curve reverts, determine the second curve to which those two points belong; Determine the mirror image of the first curve about the target turnaround point, and use the mirror image curve as the third curve; The third curve and the second curve are merged into a single target curve, such that any two points on the target curve satisfy the frequency doubling relationship between any two points before the three-dimensional curve folds back. Based on the target rotational speed, the target mode corresponding to the target rotational speed, and the harmonics, the modal frequencies of the target curve are identified.

2. The method according to claim 1, characterized in that, The mode shapes of each mode include: nodal-radius type, nodal-circle type, and a combination of nodal-radius and nodal-circle types. The rotating structure is analyzed using finite element method simulation to obtain the vibration stress of each mode, including: A three-dimensional solid model of the rotor structure is constructed using a three-dimensional model design system. The finite element analysis system is used to solve the finite element model of the three-dimensional solid model in each mode, including the pitch diameter type, pitch circle type, and the combined pitch diameter and pitch circle type.

3. The method according to claim 1 or 2, characterized in that, Based on the mode shape and vibration stress of each mode, target measurement points for all mode-specific strain gauges are determined within the rotor structure, including: Based on the mode shape and vibration stress of each mode, a preset direction is selected as the target measurement point for setting up target strain gauges for all modes.

4. The method according to claim 1, characterized in that, Vibration stress testing is performed on the target strain gauge at the target measurement points to obtain the resonance response of each mode, including: The surface location of the target measurement point is preprocessed; The target measurement point is located; The target strain gauge is attached to the target measurement point after positioning by applying adhesive. Construct a vibration stress testing system; The resonant response of each mode is obtained by slow frequency sweeping according to the maximum excitation sampling frequency.

5. The method according to claim 1, characterized in that, During the vibration stress test, the original sampling data of the target strain gauge is interpolated to determine the number of samples per revolution of the rotor structure and the corresponding octave spectrum at each sampling time, including: During the vibration stress test, the number of rotational samples per revolution was determined when interpolating the rotor structure. During the vibration stress test, the original sampling data of the target strain gauge is interpolated according to the number of rotations per week. During vibration stress testing, the target sampling data of the interpolation sampling is segmented to obtain multiple segments of sampling data; Determine each sampling time corresponding to each segment of sampled data, where each sampling time corresponds to a rotational speed; During the vibration stress test, the frequency spectrum at each sampling time is obtained by fast Fourier transform.

6. The method according to claim 1, characterized in that, Based on the modal frequencies, and in conjunction with the excitation harmonics of the rotor structure, the mode shapes of the rotor structure are identified, including: From the target curve, determine the frequency region near the excitation harmonic and identify all resonance points within that frequency region; The vibration mode of the rotor structure is identified based on the number of resonance points and the number of nodal diameters on the target curve.

7. A vibration parameter identification device for a rotor structure, characterized in that, The device includes: The vibration parameter analysis module is used to analyze the rotor structure through finite element simulation analysis to obtain the mode shape and vibration stress of each mode. The measurement location determination module is used to determine the target measurement points for all mode-specific strain gauges in the rotor structure based on the mode shape and vibration stress of each mode. The vibration stress testing module is used to perform vibration stress testing on the target strain gauge according to the target measurement point, so that the target strain gauge can obtain the resonance response of each mode. During the vibration stress testing process, the original sampling data of the target strain gauge is interpolated to determine the number of rotation samples per revolution of the rotor structure and the octave spectrum corresponding to each sampling time. The three-dimensional curve determination module is used to determine a three-dimensional curve based on the frequency harmonics corresponding to each sampling time. The three-dimensional curve is constructed by frequency harmonics, rotational speed, and amplitude. The modal frequency identification module is used to identify the modal frequencies that satisfy the preset harmonic conditions and the target curve to which the modal frequencies belong, based on the three-dimensional curve. The mode shape parameter identification module is used to identify the mode shape of the rotor structure based on the target curve and the excitation frequency harmonic of the rotor structure. The modal frequency recognition module is specifically used for: Based on the number of rotational samplings per revolution of the rotor structure, determine the target reversal point of the three-dimensional curve and the first curve to which the target reversal point belongs; Based on the frequency relationship between any two points before the three-dimensional curve reverts, determine the second curve to which those two points belong; Determine the mirror image of the first curve about the target turnaround point, and use the mirror image as the third curve; Merge the third curve and the second curve into a single target curve, and ensure that any two points on the target curve satisfy the frequency doubling relationship between any two points before the three-dimensional curve reverts to its previous state. Based on the target rotational speed, the target mode and harmonics corresponding to the target rotational speed, the modal frequencies of the target curve are identified.

8. An electronic device, characterized in that, include: A memory and a processor are interconnected, the memory stores computer instructions, and the processor executes the computer instructions to perform the vibration parameter identification method for the rotor structure according to any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions for causing the computer to execute the vibration parameter identification method for the rotor structure according to any one of claims 1 to 6.

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