Engine blade foreign object impact parameter analysis method, device, equipment and medium

Abstract

The application discloses an engine blade foreign object impact parameter analysis method, device, equipment and medium. The method comprises the following steps: acquiring actual arrival time of each calculation blade on the engine passing through each sensor, and determining rotor rotating speed of each calculation blade; determining theoretical arrival time of each calculation blade passing through each sensor according to the rotor rotating speed of each calculation blade, the installation position of each calculation blade and the installation position of each sensor; calculating vibration displacement of each calculation blade according to the theoretical arrival time, the actual arrival time and the rotor rotating speed of each calculation blade, and determining the impacted blade; acquiring time difference of the impacted blade from starting being impacted to being monitored by the sensor, and free vibration displacement, damping coefficient and resonance frequency, determining amplitude vibration parameter of the impacted blade, performing maximum amplitude backtracking reconstruction according to the amplitude vibration parameter, and solving the attenuation ratio of the backtracked maximum vibration amplitude. Through quantitative analysis of the foreign object impact, experimental research help is provided for the impact damage.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rotating blade monitoring, and in particular to an engine blade foreign object impact parameter analysis method, device, equipment and medium. BACKGROUND

[0002] Engines are key equipment for national defense and industrial production, and blades are core components of engines. The health of the blades is of great significance to the smooth, safe and efficient operation of the engines. During engine operation, blades are subjected to complex impact loads and are prone to vibration problems. Fatigue fracture failure and accidents caused by blade vibration are particularly prominent. Therefore, it is necessary to monitor the vibration of the blades. By tracking changes in parameters such as blade vibration amplitude and frequency, the purpose of fault early warning can be achieved.

[0003] Foreign object impact is an important event that affects the safe operation of engines. Monitoring the blade vibration caused by foreign object impact and identifying the vibration parameters can provide a basis for quantitative evaluation of blade damage. In the prior art, the blade tip timing algorithm is the mainstream method for monitoring blade vibration. However, due to the limited number of sensors installed on the engine, this blade tip timing algorithm based on blade tip sensors has serious undersampling, making it difficult to directly obtain the vibration parameters when the engine is subjected to foreign object impact. SUMMARY

[0004] Therefore, the purpose of the present application is to overcome the shortcomings of the prior art and provide an engine blade foreign object impact parameter analysis method, device, equipment and medium.

[0005] The present application provides the following technical solutions:

[0006] In a first aspect, the present application provides an engine blade foreign object impact parameter analysis method, which comprises:

[0007] Obtaining the actual arrival time of each calculation blade passing through each sensor on the engine, and determining the rotor speed of each calculation blade according to the actual arrival time of each calculation blade;

[0008] Determining the theoretical arrival time of each calculation blade passing through each sensor according to the rotor speed and installation position of each calculation blade, and the installation position of each sensor;

[0009] Calculating the vibration displacement of each calculation blade passing through each sensor according to the theoretical arrival time, actual arrival time and rotor speed of each calculation blade, and determining the impacted blade according to the vibration displacement of each calculation blade;

[0010] The time difference from the start of being hit to being monitored by the sensor, the free vibration displacement of the hit blade, the damping coefficient of the hit blade and the resonance frequency of the hit blade are acquired, the amplitude vibration parameter of the hit blade after being hit is determined, the maximum amplitude backtracking reconstruction is performed according to the amplitude vibration parameter, and the decay ratio of the backtracked maximum vibration amplitude is solved.

[0011] Further, the amplitude vibration parameter of the hit blade after being hit is calculated, comprising:

[0012] The calculation formula of the amplitude vibration parameter of the hit blade after being hit is:

[0013]

[0014] Wherein, A is the amplitude vibration parameter of the free vibration of the hit blade after being hit, y is the free vibration displacement, is the time difference from the start of being hit to being monitored by the sensor, ζ is the damping coefficient of the hit blade, ω i is the resonance frequency of the hit blade, and θ is a preset adjustment parameter.

[0015] Further, the hit blade is determined according to each vibration displacement, comprising:

[0016] The vibration displacement of each calculation blade is monitored, the target calculation blade in which the first abnormal vibration displacement occurs in each calculation blade is recorded, and the hit start time when the target calculation blade is hit by an external object for the first time is acquired;

[0017] The calculation blade with the most violent vibration displacement is determined as the hit blade.

[0018] Further, the time difference from the start of being hit to being monitored by the sensor is acquired, comprising:

[0019] The hit monitoring time when the hit blade appears abnormal vibration displacement is recorded;

[0020] The time difference is calculated according to the hit start time and the hit monitoring time.

[0021] Further, the free vibration displacement of the hit blade is acquired, comprising:

[0022] Based on the abnormal vibration displacement of the hit blade after being hit and the normal vibration displacement before being hit, the installation angle of each sensor is extracted;

[0023] The free vibration displacement of the hit blade is obtained by aligning the installation angle of each sensor to remove the synchronous vibration displacement.

[0024] Further, the obtaining the damping coefficient and the resonance frequency of the hit blade comprises:

[0025] According to the vibration displacement of each calculation blade and the resonance interval appearing in the engine speed-up or speed-down process, synchronous vibration parameter identification is performed to obtain the resonance speed and the frequency multiplication number of each calculation blade;

[0026] The product value of the resonance speed and the frequency multiplication number of each calculation blade is calculated, and each product value is taken as the resonance frequency of each calculation blade;

[0027] According to the number and installation position of the sensors, and the resonance frequency and the vibration displacement of each calculation blade, the damping coefficient of each calculation blade is determined.

[0028] Further, the maximum amplitude backtracking reconstruction according to the amplitude vibration parameter is performed, and the attenuation ratio of the backtracked maximum vibration amplitude is solved, comprising:

[0029] The backtracking reconstruction of the maximum positive direction vibration and the maximum negative direction vibration displacement is performed by adjusting the time difference in the calculation formula of the amplitude vibration parameter to obtain the backtracking displacement;

[0030] The backtracking displacement is compared with the vibration displacement, and the attenuation ratio of the maximum vibration amplitude is calculated according to the blade installation interval angle of each calculation blade, the installation interval angle of each sensor, and the rotor speed.

[0031] In a second aspect, an engine blade foreign object impact parameter analysis device is provided in the embodiments of the present disclosure, and the device comprises:

[0032] An acquisition module is configured to acquire actual arrival times of each calculation blade passing through each sensor on an engine, and determine rotor speeds of each calculation blade according to the actual arrival times;

[0033] A determination module is configured to determine theoretical arrival times of each calculation blade passing through each sensor according to the rotor speeds of each calculation blade, installation positions of each calculation blade, and installation positions of each sensor;

[0034] A calculation module is configured to calculate vibration displacements of each calculation blade passing through each sensor according to the theoretical arrival times, the actual arrival times, and the rotor speeds of each calculation blade, and determine a hit blade according to the vibration displacements;

[0035] A backtracking module is configured to calculate amplitude vibration parameters of the hit blade after being hit, perform maximum amplitude backtracking reconstruction according to the amplitude vibration parameters, and solve the attenuation ratio of the backtracked maximum vibration amplitude.

[0036] In a third aspect, the present disclosure provides a computer device, which comprises a memory and a processor. The memory stores a computer program. The processor executes the computer program to implement the steps of the engine blade foreign object impact parameter analysis method in the first aspect.

[0037] In a fourth aspect, the present disclosure provides a computer readable storage medium, which stores a computer program. The computer program is executed by a processor to implement the steps of the engine blade foreign object impact parameter analysis method in the first aspect.

[0038] Embodiments of the present application have the following advantages:

[0039] The engine blade foreign object impact parameter analysis method provided by the embodiments of the present application comprises the following steps: acquiring actual arrival times of each calculation blade on an engine passing through each sensor, and determining rotor speeds of each calculation blade according to the actual arrival times; determining theoretical arrival times of each calculation blade passing through each sensor according to the rotor speeds of each calculation blade and installation positions of each calculation blade and installation positions of each sensor; calculating vibration displacements of each calculation blade passing through each sensor according to the theoretical arrival times, the actual arrival times and the rotor speeds of each calculation blade, and determining an impacted blade according to the vibration displacements; acquiring a time difference from when the impacted blade is impacted to when the impacted blade is monitored by the sensor, and a free vibration displacement, a damping coefficient and a resonance frequency of the impacted blade, determining an amplitude vibration parameter of the impacted blade after being impacted, performing maximum amplitude backtracking reconstruction according to the amplitude vibration parameter, and solving a decay ratio of the backtracked maximum vibration amplitude. The present application quantitatively analyzes foreign object impact and solves the problem of backtracking of the maximum vibration displacement value of foreign object impact under undersampling caused by blade tip timing algorithm. The present application can conveniently backtrack foreign object impact signals, and can quantitatively diagnose and manage blade foreign object impact data according to the backtracked data, and provides experimental research help for impact accumulation statistics and damage, and facilitates prediction of generation of high-cycle fatigue effects caused by foreign object impact accumulation.

[0040] In order to make the above objectives, characteristics and advantages of the present application more apparent and easy to understand, the following preferred embodiments are described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0041] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some of the embodiments of the present application, and therefore should not be considered as a limitation to the scope. For those skilled in the art, other related drawings can also be obtained from these drawings without paying any creative labor. In each of the drawings, similar components are denoted by similar reference numerals.

[0042] Figure 1 A system architecture diagram in a possible application scenario provided by an embodiment of the present application is shown.

[0043] Figure 2 A flowchart of an engine blade foreign object impact parameter analysis method provided by an embodiment of the present application is shown.

[0044] Figure 3 An example diagram of a free vibration displacement and a backtracking displacement curve of a struck blade provided by an embodiment of the present application is shown.

[0045] Figure 4 A structural schematic diagram of an engine blade foreign object impact parameter analysis device provided by an embodiment of the present application is shown. DETAILED DESCRIPTION

[0046] The embodiments of the present application will be described in detail below, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary and are only used to explain the present application, and cannot be understood as a limitation to the present application.

[0047] It should be noted that when an element is referred to as being "fixed" to another element, it can be directly on the other element or there can be an intervening element. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or there can be an intervening element. In contrast, when an element is referred to as being "directly on" another element, there is no intervening element. The terms "vertical", "horizontal", "left", "right", and similar expressions used herein are for illustrative purposes only.

[0048] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connecting", "fixing" and the like should be understood in a broad sense, for example, it can be fixedly connected, or detachably connected, or integrated; it can be mechanically connected, or electrically connected; it can be directly connected, or indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0049] In addition, the terms "first", "second", etc. are used only for descriptive purposes and are not to be construed as indicating or implying relative importance or an ordered ranking of the indicated technical features. Thus, features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality" is two or more, unless otherwise explicitly and specifically limited.

[0050] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description of the template herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present application. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0051] Embodiment 1

[0052] First, the application scenarios applicable to the present application are introduced. The present application can be applied to engine blade foreign object impact quantitative diagnosis, and the maximum vibration amplitude of the blade impacted by the foreign object is traced back to facilitate the statistical and management of impact cumulative data and the study of the influence of high-cycle fatigue effect caused by impact on blade life. Please refer to Figure 1 , Figure 1 A system composition in the application scenario is shown in Figure 1 The system includes an engine blade foreign object impact parameter analysis device, an application server and a plurality of engines. The analysis device is connected with the application server and can call various data from the application server, such as various operating data of the engine. It can be understood that in the above example, the analysis device is connected with the server and data is called from the server, but in other examples, the analysis device can also be connected with the server while being directly connected with each engine or a database, etc. to call the data of the engine, which is not limited by the present application.

[0053] As shown in Figure 2 , it is a flow chart of an engine blade foreign object impact parameter analysis method in an embodiment of the present application. The engine blade foreign object impact parameter analysis method provided by the present application includes the following steps:

[0054] Step S110, the actual arrival time of each calculation blade on the engine passing through each sensor is obtained, and the rotor speed of each calculation blade is determined according to the actual arrival time.

[0055] In the embodiments of the present application, first, any blade on the engine is determined as No. 1 blade, and all blades are numbered in the counterclockwise direction, and all blades are calculation blades. Generally, the motion of all calculation blades is divided into rotation and vibration in the angular domain, as shown in formula 1:

[0056] ψ(t) = φ1(t) + φ2(t) (Formula 1)

[0057] In the formula, ψ(t) is the total radian of the tip motion of the calculation blade, φ1(t) is the radian of the cumulative rotation of the calculation blade, and φ2(t) is the radian offset caused by the tip vibration of the calculation blade.

[0058] The calculation formula of the radian of the cumulative rotation of the calculation blade φ1(t) is shown in formula 2:

[0059]

[0060] In the formula, Ω(t) is the rotor speed of the calculation blade, unit is Hz, t 0(n) is the start time of the n th rotation of the calculation blade, t 1(n) represents the end time of the n th rotation of the calculation blade.

[0061] The calculation formula of the radian offset caused by the tip vibration of the calculation blade φ2(t) is shown in formula 3:

[0062]

[0063] In the formula, R is the distance from the tip to the center of the blade disc, and y(t) is the tip vibration displacement of the calculation blade.

[0064] In the traditional tip timing method, the rotor speed of the calculation blade is calculated by the time difference between two pulse signals of the key phase sensor, and only one rotor speed value is generated in one rotation. Considering the rotor speed fluctuation, the rotor speed Ω(t) is considered as a constant acceleration process, as shown in formula 4:

[0065] Ω(t) = a (n) t + f 0(n) (Formula 4)

[0066] In the formula, a (n) is the speed change rate of the calculation blade in the n th rotation, that is, the acceleration, unit is Hz / s, is the rotor speed of the calculation blade at the start of the n th rotation, unit is Hz.

[0067] In step S120, according to the rotor speed and the installation position of each calculation blade, and the installation position of each sensor, the theoretical arrival time of each calculation blade passing through each sensor is determined.

[0068] Step S130, according to the theoretical arrival time, the actual arrival time and the rotor speed of each calculation blade, the vibration displacement of each calculation blade passing through each sensor is calculated, and the hit blade is determined according to the vibration displacement.

[0069] When the calculation blade does not vibrate, the theoretical arrival time of each calculation blade passing through each sensor can be calculated by the rotor speed, the installation position of the sensor and the blade. The actual arrival time of the calculation blade passing through the sensor is inconsistent with the theoretical arrival time due to the existence of the blade tip vibration, and the difference is caused by the blade tip vibration, so the vibration displacement y of the calculation blade can be calculated. (n，b) As shown in formula 5:

[0070] y (n，b) = (t (n，b) -t th(n，b) )·v (n) (Formula 5)

[0071] In the formula, v (n) represents the linear speed of the calculation blade at the nth turn, y (n，b) represents the vibration displacement of the bth calculation blade at the nth turn, t (n，b) is the actual arrival time of the bth calculation blade at the nth turn passing through the sensor, t th(n，b) is the theoretical arrival time of the bth calculation blade at the nth turn passing through the sensor.

[0072] It should be noted that in the embodiments of the present application, Wherein, R is the distance from the tip of the calculation blade to the axis of the blade disc.

[0073] Further, after calculating the vibration displacement of the calculation blade, according to the vibration displacement of each calculation blade and the resonance interval appearing in the process of engine speed-up or speed-down, synchronous vibration parameter identification is carried out to obtain the resonance speed and the frequency multiplication number of each calculation blade. The product value of the resonance speed and the frequency multiplication number of each calculation blade is calculated, and each product value is taken as the resonance frequency of the corresponding calculation blade. At the same time, according to the number and installation position of the sensor, as well as the resonance frequency and the vibration displacement of each calculation blade, the damping coefficient of each calculation blade is determined.

[0074] Tip timing as a non-contact rotating blade vibration measurement method has been proved to be an effective measurement method by many studies. The method installs a number of sensors on the engine casing at certain angles, and the time when the blade rotates to the sensor is captured and recorded. The time when the blade arrives at the sensor without vibration can be calculated theoretically. When the blade vibrates, the time when the blade arrives at the sensor will be ahead or lag. According to the difference between the theoretical arrival time and the actual arrival time and the rotor speed, a vibration displacement sequence composed of multiple vibration displacements can be converted, so as to further analyze the vibration displacement sequence.

[0075] According to the above tip timing measurement principle, the sensor samples once every time the blade rotates one circle. It is specified that the calculated blade passing through the No. 1 sensor at 0 o'clock is No. 1 blade, and the installation angle thereof is 0. It is assumed that the installation angle of the No. p sensor relative to the No. 1 sensor is Then, the arrival time t of the No. b calculated blade recorded by the No. p sensor in the jth circle is j,, As shown in formula 6:

[0076]

[0077] In the formula, is the initial angle of the No. b calculated blade, is the theoretical installation position of the sensor.

[0078] All calculated blades in a coordinated bladed disc of an engine are uniformly and equally spaced, so The expression of is shown in formula 7:

[0079]

[0080] In the formula, N B is the number of blades of the No. b calculated blade.

[0081] It should be noted that formula 6 is the arrival time of the No. b calculated blade recorded by the No. p sensor in the jth circle without considering the installation error of the calculated blade and the installation error of the sensor. However, due to the influence of machining, installation and other errors, the actual installation position of the calculated blade and the installation position of the sensor will always deviate. Considering the influence of installation error, the actual installation angle of the sensor As shown in formula 8:

[0082]

[0083] In the formula, is the theoretical installation position of the No. p sensor, is the installation deviation of the No. p sensor.

[0084] Considering the machining installation error of the calculation blade, the actual initial angle of the bth calculation blade is calculated The expression is shown as equation 9:

[0085]

[0086] In the equation, N B is the number of blades of the bth calculation blade, is the installation angle deviation of the bth calculation blade.

[0087] Considering the installation error of the calculation blade and the installation error of the sensor, then according to equation 6, the theoretical arrival time of the bth calculation blade recorded by the pth sensor in the jth turn As shown in equation 10:

[0088]

[0089] The synchronous vibration displacement of the bth calculation blade under the action of the single airflow excitation force calculated by the pth sensor in the jth turn As shown in equation 11:

[0090]

[0091] In the equation, C b is the maximum vibration amplitude of the bth calculation blade under the action of all airflow excitation forces, |H(ω b )| is the amplitude-frequency response of the bth calculation blade, ω b is the resonance frequency of the bth calculation blade, EO b is the multiple frequency of the bth calculation blade, is the phase-frequency response of the bth calculation blade, φ b is the phase difference between the bth calculation blade and the closest excitation source at zero time, D b is the synchronous vibration constant bias of the bth calculation blade.

[0092] According to equation 11 and the rotor speed of the bth calculation blade at this moment, the actual arrival time of the bth calculation blade to the pth sensor in the jth turn can be obtained As shown in equation 12:

[0093]

[0094] In the equation, V(j) represents the rotor speed of the calculation blade in the jth turn.

[0095] Further, the vibration displacement of each of the calculation blades is monitored, and when an external object strikes, a target calculation blade in which abnormal vibration displacement first occurs among the calculation blades is recorded, and a striking start time when the target calculation blade is first monitored by the sensor to be struck by the external object is acquired. The i-th calculation blade is a struck blade, and the i-th calculation blade suffers from an external object strike in the n-th revolution. The striking start time of the i-th calculation blade acquired by the p-th sensor is As shown in formula 13:

[0096]

[0097] In the formula, is the theoretical striking start time of the i-th calculation blade acquired by the p-th sensor, is the actual installation angle of the p-th sensor, is the actual installation angle of the i-th calculation blade, d FOD is the percentage of the duration of the external object strike in the time required for one revolution of the calculation blade rotor, and the calculation formula is

[0098] The installation angles of the sensors are aligned to remove the synchronous vibration displacement. By substituting formula 13 into the free vibration formula after the strike, the free vibration displacement of the i-th calculation blade calculated by the p-th sensor data is As shown in formula 14:

[0099]

[0100] In the formula, y (n，b) represents the vibration displacement of the b-th calculation blade in the n-th revolution, is the synchronous vibration displacement of the b-th calculation blade under the action of the airflow excitation force alone calculated by the p-th sensor in the j-th revolution.

[0101] The vibration displacement calculated from the actual arrival time measured by the struck blade contains the synchronous vibration displacement and the free vibration displacement after the strike ends. By linearly superimposing the two, the actual striking start time when the i-th calculation blade is simultaneously acted upon by the two can be calculated, that is, the actual striking start time when the i-th calculation blade passes through the p-th sensor in the j-th revolution As shown in formula 15:

[0102]

[0103] In the formula, is the theoretical arrival time of the i-th calculation blade passing through the p-th sensor in the j-th revolution, is the synchronous vibration displacement of the i-th calculation blade calculated by the p-th sensor data.

[0104] Further, the hitting monitoring moment at which the abnormal vibration displacement of the hit blade occurs is recorded, and the time difference t of the hit blade from the hitting starting moment to the monitored moment is calculated according to the hitting starting moment and the hitting monitoring moment (j-n)，p，i As shown in formula 16:

[0105] t (j-n)，p，i = t j，p，i -t n，px，i1 (Formula 16)

[0106] In the formula, t j，p，i is the hitting monitoring moment of the ith calculation blade monitored by the pth sensor at the jth turn, t n，px，i1 is the hitting starting moment of the ith1 calculation blade monitored by the pxth sensor at the nth turn after the hitting, and it is to be noted that j>n, n is the turn number of the hitting monitored, which is a fixed number, and j is the rotor rotation turn number which increases with rotation.

[0107] In step S140, the time difference of the hit blade from the hitting starting moment to the monitored moment by the sensor, the free vibration displacement, the damping coefficient and the resonance frequency of the hit blade are obtained, the amplitude vibration parameter of the hit blade after the hitting is determined, the maximum amplitude backtracking reconstruction is performed according to the amplitude vibration parameter, and the decay ratio is solved for the backtracked maximum vibration amplitude.

[0108] In the embodiment of the present application, the vibration displacement calculated by the actual arrival moment of the hit blade contains the synchronous vibration displacement and the free vibration displacement after the hitting ending, therefore, the vibration displacement after the hitting of the hit blade is first desynchronized, and then fitted, and the As x, the actually measured vibration displacement is Y, and the fitting as shown in formula 17 is performed:

[0109] Y = Ax + b (Formula 17)

[0110] According to formula 14 and formula 17, the calculation formula of the amplitude vibration parameter A of the hit blade, i.e. the ith calculation blade after the hitting, is shown in formula 18:

[0111]

[0112] In the formula, A is the amplitude vibration parameter of the free vibration of the hit blade after the hitting, y is the free vibration displacement, is the time difference of the hit blade from the hitting starting moment to the monitored moment by the sensor, ζ is the damping coefficient of the hit blade, ω i is the resonance frequency of the hit blade, and θ is a preset adjustment parameter.

[0113] It should be noted that θ, as a preset adjustment parameter, is mainly used to adjust the angle of the fitted data so that the fitted data can basically match the data measured by the sensor. In the actual fitting process, the angle overlap and the correlation coefficient between the original sensor data and the fitted data are also combined to judge the fitting effect to ensure the correctness of the fitting.

[0114] The impact event is traced back based on the amplitude vibration parameters. The maximum positive and maximum negative vibration displacements are traced by adjusting the time difference in the calculation formula of the amplitude vibration parameters. The traced displacements are plotted and compared with the vibration displacements. Based on the blade installation interval angles of each calculated blade, the installation interval angles of each sensor, and the rotor speed, the attenuation ratio of the maximum vibration amplitude is calculated. The attenuation percentage η of the maximum vibration amplitude is shown in Equation 19 below:

[0115]

[0116] In the formula, The maximum installation angle difference between the two calculated blades, f is the minimum installation angle difference between the two sensors. rotor The rotor frequency of the blades is calculated in Hz.

[0117] For example, an impact test was conducted on a torsion blade test bench at a rotor speed of 3500 rpm using the method of this embodiment. During the process of calculating the displacement data of the impacted blade back to its original position based on various given parameters, the following results were obtained: Figure 3 The comparison chart.

[0118] from Figure 3 As can be seen, the trend of the displacement data after retrospection is basically consistent with that of the vibration displacement (BBT) data. By solving the correlation coefficient between the two sets of data, the result is 0.9657. Figure 3 The first positive peak and the first negative peak in the backtracking data curve represent the maximum positive vibration and the maximum negative vibration displacement of the blade after it has been struck by a foreign object. Based on the backtracking data, quantitative diagnosis and management of the blade's foreign object impact data can be carried out, and experimental research assistance can be provided for damage accumulation.

[0119] The engine blade impact parameter analysis method provided in this application embodiment obtains the actual arrival time of each calculated blade on the engine passing through each sensor, and determines the rotor speed of each calculated blade based on the actual arrival time; determines the theoretical arrival time of each calculated blade passing through each sensor based on the rotor speed and installation position of each calculated blade, as well as the installation position of each sensor; calculates the vibration displacement of each calculated blade passing through each sensor based on the theoretical arrival time, actual arrival time, and rotor speed of each calculated blade, and determines the impacted blade based on the vibration displacement; obtains the time difference from the impact to the detection by the sensor, as well as the free vibration displacement, damping coefficient, and resonant frequency of the impacted blade, determines the amplitude vibration parameters of the impacted blade after the impact, performs maximum amplitude backtracking reconstruction based on the amplitude vibration parameters, and solves the attenuation ratio of the backtracked maximum vibration amplitude. This invention provides a quantitative analysis of external object impacts and solves the problem of backtracking the maximum vibration displacement value of external object impacts under undersampling caused by the blade tip timing algorithm. It can easily backtrack external object impact signals, and the backtracked data can be used for quantitative diagnosis and management of blade external object impact data. It also provides experimental research assistance for impact accumulation statistics and damage, and facilitates the prediction of the high-cycle fatigue effect caused by the accumulation of external object impacts.

[0120] Example 2

[0121] like Figure 4 The diagram shown is a structural schematic of an engine blade foreign object impact parameter analysis device 400 according to an embodiment of this application. The device includes:

[0122] The acquisition module 410 is used to acquire the actual arrival time of each computing blade on the engine after passing each sensor, and to determine the rotor speed of each computing blade based on the actual arrival time.

[0123] The determining module 420 is used to determine the theoretical arrival time of each of the calculated blades after passing each of the sensors based on the rotor speed, installation position, and installation position of each of the calculated blades;

[0124] The calculation module 430 is used to calculate the vibration displacement of each of the calculated blades after passing through each of the sensors based on the theoretical arrival time, actual arrival time and rotor speed of each of the calculated blades, and to determine the blade being struck based on the vibration displacement.

[0125] The backtracking module 440 is used to calculate the amplitude vibration parameters of the struck blade after it is struck, perform maximum amplitude backtracking reconstruction based on the amplitude vibration parameters, and solve for the attenuation ratio of the backtracked maximum vibration amplitude.

[0126] Optionally, the engine blade foreign object impact parameter analysis device further comprises:

[0127] A parameter calculation module is configured to calculate the amplitude vibration parameter of the impacted blade after being impacted according to the following formula:

[0128]

[0129] wherein A is the amplitude vibration parameter of the free vibration of the impacted blade after being impacted, y is the free vibration displacement, is a time difference from the start of being impacted to the time when the impacted blade is monitored by the sensor, ζ is the damping coefficient of the impacted blade, ω i is the resonance frequency of the impacted blade, and θ is a preset adjustment parameter.

[0130] Optionally, the engine blade foreign object impact parameter analysis device further comprises:

[0131] A first recording module is configured to monitor the vibration displacement of each calculation blade, record a target calculation blade in which the first abnormal vibration displacement occurs, and obtain an impact start time when the target calculation blade is impacted by a foreign object for the first time and monitored by the sensor.

[0132] A second recording module is configured to determine the calculation blade with the most severe vibration displacement as the impacted blade, and record an impact monitoring time when the abnormal vibration displacement of the impacted blade occurs.

[0133] A time difference calculation module is configured to calculate the time difference according to the impact start time and the impact monitoring time.

[0134] Optionally, the engine blade foreign object impact parameter analysis device further comprises:

[0135] An extraction module is configured to extract the installation angle of each sensor based on the abnormal vibration displacement of the impacted blade after being impacted and the normal vibration displacement before being impacted.

[0136] A removal module is configured to remove the synchronous vibration displacement by aligning the installation angle of each sensor to obtain the free vibration displacement of the impacted blade.

[0137] Optionally, the engine blade foreign object impact parameter analysis device further comprises:

[0138] An identification module is configured to identify the synchronous vibration parameter according to the vibration displacement of each calculation blade and the resonance interval occurring in the engine speed-up or speed-down process to obtain the resonance speed and the frequency multiplication number of each calculation blade.

[0139] A frequency calculation module is configured to calculate a product value of a resonance rotating speed and a frequency multiplication number of each of the calculation blades, and take each of the product values as a resonance frequency of each of the calculation blades.

[0140] Optionally, the engine blade foreign object impact parameter analysis device further comprises:

[0141] A coefficient calculation module is configured to determine a damping coefficient of each of the calculation blades according to the number and installation positions of the sensors, and the resonance frequencies and vibration displacements of each of the calculation blades.

[0142] Optionally, the engine blade foreign object impact parameter analysis device further comprises:

[0143] A reconstruction module is configured to perform backtracking reconstruction of the maximum positive direction vibration displacement and the maximum negative direction vibration displacement by adjusting a time difference in a calculation formula of the amplitude vibration parameter, to obtain a backtracking displacement.

[0144] An attenuation module is configured to compare the backtracking displacement with the vibration displacement, and calculate an attenuation ratio of the maximum vibration amplitude according to a blade installation interval angle of each of the calculation blades, a sensor installation interval angle of each of the sensors, and the rotating speed of the rotor.

[0145] The engine blade foreign object impact parameter analysis device provided by the embodiments quantitatively analyzes the foreign object impact, solves the problem of backtracking of the maximum vibration displacement value of the foreign object impact under under-sampling caused by the blade tip timing algorithm, and can conveniently backtrack the foreign object impact signal. Quantitative diagnosis and management of the blade foreign object impact data can be performed according to the backtracked data, and experimental research assistance is provided for impact accumulation statistics and damage, which facilitates prediction of generation of high-cycle fatigue effects caused by foreign object impact accumulation.

[0146] In the embodiments of the present disclosure, a computer device is provided, which includes a memory and a processor. The memory stores a computer program, and the processor implements the steps of the engine blade foreign object impact parameter analysis method described in Embodiment 1 when executing the computer program.

[0147] In the embodiments of the present disclosure, a computer readable storage medium is provided, which stores a computer program. The computer program is executed by a processor to implement the steps of the engine blade foreign object impact parameter analysis method described in Embodiment 1.

[0148] In several embodiments provided in the present application, it should be understood that the disclosed apparatus and method can also be implemented by other manners. The apparatus embodiments described above are merely illustrative, for example, the flowcharts and structural diagrams in the drawings show the possible implementation architecture, function and operation of the apparatus, method and computer program product according to the embodiments of the present application. In this regard, each block in the flowchart or block diagram can represent a module, a program segment or a part of code, which contains one or more executable instructions for implementing the specified logic function. It should also be noted that in alternative implementation manners, the functions noted in the blocks can also occur in different order from that noted in the drawings. For example, two consecutive blocks can actually be executed substantially in parallel, and they can also be executed in reverse order, depending on the functions involved. It should also be noted that each block in the structural diagram and / or flowchart, and the combination of blocks in the structural diagram and / or flowchart, can be implemented by a dedicated hardware-based system for executing the specified function or action, or can be implemented by a combination of dedicated hardware and computer instructions.

[0149] In addition, each functional module or unit in the embodiments of the present application can be integrated together to form an independent part, or each module can exist independently, or two or more modules can be integrated to form an independent part.

[0150] If the functions are implemented in the form of software function modules and sold or used as independent products, they can be stored in a computer readable storage medium. Based on this understanding, the technical solutions of the present application essentially or the part of the prior art that contributes to the technical solutions or the part of the technical solutions can be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for causing a computer device (which can be a smart phone, a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the embodiments of the present application. The aforementioned storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and various media that can store program codes.

[0151] The above description is merely a specific implementation of the present application, but the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of changes or replacements within the technical range disclosed in the present application, which should be covered within the protection scope of the present application.

Claims

1. An engine blade foreign object strike parameter analysis method, characterized by, The method comprises: acquiring actual arrival time of each calculation blade on the engine passing each sensor, and determining rotor speed of each calculation blade according to the actual arrival time; determining theoretical arrival time of each calculation blade passing each sensor according to rotor speed and installation position of each calculation blade, and installation position of each sensor; calculating vibration displacement of each calculation blade passing each sensor according to theoretical arrival time, actual arrival time and rotor speed of each calculation blade, and determining hit blade according to the vibration displacement; acquiring time difference from start of the hit blade being hit to being monitored by the sensor, and determining amplitude vibration parameter of the hit blade after being hit according to free vibration displacement, damping coefficient and resonance frequency of the hit blade, performing maximum amplitude backtracking reconstruction according to the amplitude vibration parameter, and solving decay ratio of the backtracked maximum vibration amplitude; the determination of the hit blade according to the vibration displacement comprises: monitoring vibration displacement of each calculation blade, recording target calculation blade in which first abnormal vibration displacement occurs in each calculation blade, and acquiring hit start time when the target calculation blade is hit by foreign matter for the first time and monitored by the sensor; determining calculation blade with most severe vibration displacement as the hit blade.

2. The engine blade foreign object strike parameter analysis method of claim 1, wherein, the calculation of the amplitude vibration parameter of the hit blade after being hit comprises: the calculation formula of the amplitude vibration parameter of the hit blade after being hit is: wherein, is a free vibration amplitude parameter of the free vibration of the hit blade after being hit, is a free vibration displacement, is a time difference from the start of the hit to the time when the hit blade is monitored by the sensor, is a damping coefficient of the hit blade, is a resonance frequency of the hit blade, is a preset adjustment parameter.

3. The engine blade foreign object strike parameter analysis method of claim 2, wherein, the acquisition of the time difference from the start of the hit blade being hit to being monitored by the sensor comprises: recording hit monitoring time when abnormal vibration displacement of the hit blade occurs; calculating the time difference according to the hit start time and the hit monitoring time.

4. The engine blade foreign object strike parameter analysis method of claim 3, wherein, the acquisition of the free vibration displacement of the hit blade comprises: extracting installation angle of each sensor based on abnormal vibration displacement of the hit blade after being hit and normal vibration displacement of the hit blade before being hit; aligning installation angle of each sensor to remove synchronous vibration displacement, and obtaining the free vibration displacement of the hit blade.

5. The engine blade foreign object strike parameter analysis method of claim 4, wherein, the acquisition of the damping coefficient and the resonance frequency of the hit blade comprises: performing synchronous vibration parameter identification according to vibration displacement of each calculation blade and resonance interval appearing in the engine speed-up or speed-down process, and obtaining resonance speed and frequency multiplication number of each calculation blade; calculating product value of resonance speed and frequency multiplication number of each calculation blade, and taking each product value as resonance frequency of each calculation blade; determining damping coefficient of each calculation blade according to number and installation position of the sensors, and resonance frequency and vibration displacement of each calculation blade.

6. The engine blade foreign object strike parameter analysis method of claim 5, wherein, the maximum amplitude backtracking reconstruction according to the amplitude vibration parameter and the solving of decay ratio of the backtracked maximum vibration amplitude comprise: performing backtracking reconstruction of maximum positive direction vibration and maximum negative direction vibration displacement by adjusting time difference in the calculation formula of the amplitude vibration parameter, and obtaining backtracking displacement; The maximum vibration amplitude decay ratio is calculated by comparing the backtracking displacement and the vibration displacement, and according to the blade installation interval angle of each calculation blade, the installation interval angle of each sensor, and the rotor speed.

7. An engine blade foreign object strike parameter analysis apparatus, characterized by, The device comprises: An acquisition module is configured to acquire actual arrival time of each calculation blade passing each sensor on the engine, and determine rotor speed of each calculation blade according to the actual arrival time; A determination module is configured to determine theoretical arrival time of each calculation blade passing each sensor according to rotor speed, installation position of each calculation blade, and installation position of each sensor; A calculation module is configured to calculate vibration displacement of each calculation blade passing each sensor according to theoretical arrival time, actual arrival time, and rotor speed of each calculation blade, and determine a hit blade according to the vibration displacement; A backtracking module is configured to acquire time difference from the start of being hit to being monitored by the sensor of the hit blade, and free vibration displacement, damping coefficient, and resonance frequency of the hit blade, calculate amplitude vibration parameter of the hit blade after being hit, perform maximum amplitude backtracking reconstruction according to the amplitude vibration parameter, and solve the decay ratio of the backtracked maximum vibration amplitude. The engine blade foreign object hit parameter analysis device further comprises: A first recording module is configured to monitor vibration displacement of each calculation blade, record a target calculation blade in which abnormal vibration displacement first occurs among each calculation blade, and acquire hit start time when the target calculation blade is hit by a foreign object for the first time and monitored by the sensor; A second recording module is configured to determine the calculation blade with the most severe vibration displacement as the hit blade.

8. A computer device, comprising: The device comprises a memory and a processor, the memory stores a computer program, and the processor implements the steps of the engine blade foreign object hit parameter analysis method in any one of claims 1-6 when executing the computer program.

9. A computer-readable storage medium, characterized in that, The computer readable storage medium stores a computer program, and the computer program implements the steps of the engine blade foreign object hit parameter analysis method in any one of claims 1-6 when executed by the processor.

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