Aero-engine blade data storage method, device, equipment and medium

Abstract

The invention discloses an aero-engine blade data storage method, device and equipment and a medium, and relates to the technical field of data processing. The method comprises the steps that signals of all blades of the aero-engine are collected through a plurality of sensors, and blade vibration signals and blade tip gap signals corresponding to the sensors are obtained; generating health characteristic parameters corresponding to the sensors according to the blade vibration signals and the blade tip gap signals corresponding to the sensors, and generating signal auxiliary information corresponding to the sensors according to the health characteristic parameters; determining a time cache granularity corresponding to each sensor according to each piece of signal subsidiary information, and allocating a continuous address cache region corresponding to each sensor; and storing a blade vibration signal, a blade tip gap signal, a health characteristic parameter and signal affiliated information corresponding to each sensor according to each time cache granularity and each continuous address cache region. In this way, efficient and low-redundancy storage can be achieved, and high real-time performance and flexible expansion are achieved.

Description

Technical Field

[0001] The present invention relates to the field of data processing technology, and in particular to a method, device, equipment and medium for storing data of an aircraft engine blade. Background Art

[0002] During operation, aircraft engine blades are subjected to extreme conditions such as high temperature, high pressure, and high rotational speed. Blade vibration and tip clearance can reflect their health status and assess their safety. Monitoring blade vibration and tip clearance often requires collecting multi-channel signal data at a high sampling rate, performing high-speed processing and storage, and assessing in real time whether the blades are experiencing fatigue, cracks, and other issues. However, existing technologies often rely on the CPU for data processing, and storage systems typically use traditional hard disks or software-managed file systems. This presents the following problems: Because aircraft engine signals are coupled, the CPU can only process multi-channel data serially, failing to meet the real-time requirements of high-speed blade signals. Traditional storage methods are not optimized for multi-channel data, resulting in a large portion of the stored data being redundant and relying entirely on the CPU to schedule data writes. This results in slow data write speeds, severe fragmentation, and the risk of write failure when CPU resources are insufficient. Summary of the Invention

[0003] In view of this, the purpose of the present invention is to overcome the deficiencies in the prior art and provide an aircraft engine blade data storage method, device, equipment and medium for high-speed data processing and storage during aircraft engine blade health monitoring.

[0004] The present invention provides the following technical solutions:

[0005] In a first aspect, the present invention provides a method for storing data of an aircraft engine blade, comprising:

[0006] The signals of all blades of the aircraft engine are collected by multiple sensors respectively, and the blade vibration signals and blade tip clearance signals corresponding to the sensors are obtained;

[0007] generating health characteristic parameters corresponding to each sensor according to the blade vibration signals and blade tip clearance signals corresponding to each sensor, and generating signal auxiliary information corresponding to each sensor according to each health characteristic parameter;

[0008] Determining a time buffer granularity corresponding to each of the sensors according to the attached information of each signal, and allocating a continuous address buffer area corresponding to each of the sensors;

[0009] The target signal set corresponding to each sensor is stored according to each time cache granularity and each continuous address cache area, and the target signal set includes at least two of the blade vibration signal, the blade tip clearance signal, the health characteristic parameter and the signal auxiliary information.

[0010] In one embodiment, the health characteristic parameter includes a voltage amplitude sampled at equal intervals, and the signal ancillary information includes a blade tip signal characteristic value;

[0011] Generating health characteristic parameters corresponding to each sensor according to the blade vibration signal and the blade tip clearance signal corresponding to each sensor, and generating signal auxiliary information corresponding to each sensor according to each health characteristic parameter, includes:

[0012] For each of the sensors, performing sliding window filtering on the blade tip clearance signal to obtain a filtered blade tip clearance signal;

[0013] Performing equal-interval voltage amplitude extraction on the filtered tip clearance signal to obtain the equal-interval sampling voltage amplitude;

[0014] The maximum value of all equally spaced sampled voltage amplitudes of each blade in each circle is taken as the blade tip signal characteristic value.

[0015] In one embodiment, determining the time buffer granularity corresponding to each sensor according to the auxiliary information of each signal, and allocating a continuous address buffer area corresponding to each sensor, includes:

[0016] For each of the sensors, calculating a characteristic value change rate according to the blade tip signal characteristic value;

[0017] Determining a change rate grading index according to the characteristic value change rate;

[0018] The characteristic value change rate is graded according to a preset classification threshold and the change rate classification index, the time cache granularity is determined according to the classification result, and the continuous address cache area is allocated.

[0019] In one embodiment, calculating the characteristic value change rate based on the blade tip signal characteristic value includes:

[0020] Calculate the absolute value of the difference between the blade tip signal characteristic value at the current circle timestamp and the blade tip signal characteristic value at the previous circle timestamp;

[0021] Calculate the difference between the current circle timestamp and the previous circle timestamp as the interval time;

[0022] The quotient of the absolute value of the difference and the interval time is calculated as the characteristic value change rate.

[0023] In one embodiment, determining a change rate grading index based on the characteristic value change rate includes:

[0024] Calculate the range of all equally spaced voltage amplitudes sampled at the current timestamp and the range of all equally spaced voltage amplitudes sampled at the previous timestamp;

[0025] The quotient of the characteristic value change rate and the range is calculated as the change rate grading index.

[0026] In one embodiment, the preset classification threshold includes a first classification threshold and a second classification threshold, and grading the characteristic value change rate according to the preset classification threshold and the change rate classification index, determining the time cache granularity according to the classification result, and allocating the continuous address cache area include:

[0027] If the change rate classification index is greater than or equal to the first classification threshold, determining the time cache granularity to be the first time granularity, and allocating the continuous address cache area as the first cache area; the first cache area is used to store the signal auxiliary information and the health characteristic parameter;

[0028] If the change rate classification index is greater than or equal to the second classification threshold and less than or equal to the first classification threshold, determining the time cache granularity to be the second time granularity and allocating the continuous address cache area as the second cache area; the second cache area is used to store the tip clearance signal, the signal ancillary information, and the health characteristic parameter;

[0029] If the change rate classification index is less than or equal to the second classification threshold, determining the time cache granularity to be a third time granularity and allocating the continuous address cache area to be a third cache area; the third cache area is used to store the blade vibration signal and the blade tip clearance signal;

[0030] The third time granularity, the second time granularity and the first time granularity decrease in sequence.

[0031] In one embodiment, the health characteristic parameters include edge timestamps and tip clearance signal frequencies, and the signal ancillary information includes sampling rate, data storage format, acquisition channel number, sampling point timestamps of the equally spaced voltage amplitudes, and the number of sampling points.

[0032] In a second aspect, the present invention provides an aircraft engine blade data storage device, comprising:

[0033] An acquisition module is used to respectively acquire signals from all blades of the aircraft engine through multiple sensors to obtain blade vibration signals and blade tip clearance signals corresponding to each of the sensors;

[0034] a processing module, configured to generate health characteristic parameters corresponding to each of the sensors based on the blade vibration signals and blade tip clearance signals corresponding to each of the sensors, and to generate signal ancillary information corresponding to each of the sensors based on each of the health characteristic parameters;

[0035] a determination module, configured to determine a time buffer granularity corresponding to each of the sensors according to the attached information of each signal, and to allocate a continuous address buffer area corresponding to each of the sensors;

[0036] A storage module is used to store the target signal set corresponding to each of the sensors according to each of the time cache granularities and each of the continuous address cache areas, wherein the target signal set includes at least two of the blade vibration signal, the tip clearance signal, the health characteristic parameter and the signal ancillary information.

[0037] In a third aspect, the present invention provides a computer device comprising a memory and a processor, wherein the memory stores a computer program, and when the computer program is executed by the processor, the method for storing aircraft engine blade data as described in the first aspect is implemented.

[0038] In a fourth aspect, the present invention provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the method for storing aircraft engine blade data as described in the first aspect.

[0039] The present invention discloses a method, apparatus, device, and medium for storing data on aircraft engine blades. Multiple sensors are used to collect signals from all aircraft engine blades, obtaining blade vibration signals and tip clearance signals corresponding to each sensor. Health characteristic parameters corresponding to each sensor are generated based on the blade vibration and tip clearance signals corresponding to each sensor, and signal ancillary information corresponding to each sensor is generated based on the health characteristic parameters. Time cache granularity corresponding to each sensor is determined based on the signal ancillary information, and a continuous address cache area is allocated to each sensor. Target signal sets corresponding to each sensor are stored based on the time cache granularity and the continuous address cache area. The target signal sets include at least two of the blade vibration signal, the tip clearance signal, the health characteristic parameters, and the signal ancillary information. In this way, the blade vibration and tip clearance signals collected by each sensor are preprocessed to obtain health characteristic parameters and signal ancillary information. The signal ancillary information is then used to set a time cache granularity and a continuous address cache area for each sensor's signal, achieving efficient, low-redundancy storage with high real-time performance and flexible expansion. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the technical solution of the present invention, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present invention and should not be regarded as limiting the scope of protection of the present invention. In each of the drawings, similar components are numbered similarly.

[0041] Figure 1 A schematic diagram showing a flow chart of the method for storing data of an aircraft engine blade proposed in this embodiment is shown;

[0042] Figure 2 A schematic diagram of the blade vibration signal and the blade tip clearance signal proposed in this embodiment is shown;

[0043] Figure 3 FIG. 4 shows a schematic diagram of extracting health characteristic parameters proposed in this embodiment;

[0044] Figure 4 A schematic diagram of the data frame memory arrangement format proposed in this embodiment is provided;

[0045] Figure 5 Another schematic diagram of the flow chart of the method for storing data of an aircraft engine blade proposed in this embodiment is shown;

[0046] Figure 6 A schematic diagram of the storage process proposed in this embodiment is shown;

[0047] Figure 7 A structural schematic diagram of the aircraft engine blade data storage device proposed in this embodiment is shown.

[0048] Description of the accompanying drawings:

[0049] 700 - aircraft engine blade data storage device; 701 - acquisition module; 702 - processing module; 703 - determination module; 704 - storage module. DETAILED DESCRIPTION

[0050] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0051] The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a variety of different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the figures is not intended to limit the scope of the claimed invention, but rather merely represents selected embodiments of the present invention. All other embodiments derived by those skilled in the art based on the embodiments of the present invention without inventive effort are intended to be within the scope of protection of the present invention.

[0052] Hereinafter, the terms "including", "having" and their cognates, which may be used in various embodiments of the present invention, are intended only to indicate specific features, numbers, steps, operations, elements, components or combinations of the foregoing items, and should not be understood as first excluding the existence of one or more other features, numbers, steps, operations, elements, components or combinations of the foregoing items or the possibility of adding one or more features, numbers, steps, operations, elements, components or combinations of the foregoing items.

[0053] Furthermore, the terms “first,” “second,” “third,” etc., are merely used for distinguishing descriptions and are not to be understood as indicating or implying relative importance.

[0054] Unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by those skilled in the art to which the various embodiments of the present invention pertain. The terms (such as those defined in generally used dictionaries) will be interpreted as having the same meaning as in the context of the relevant technical field and will not be interpreted as having an idealized meaning or an overly formal meaning unless clearly defined in the various embodiments of the present invention.

[0055] Example 1

[0056] The number of blades of the aircraft engine is 45, the blade radius is 145,000 microns, the cruising speed is 35,000 revolutions per minute, and the average monitoring time of a single operation is 1 hour.

[0057] During engine operation, laser signals are primarily used to acquire digital blade vibration signals, with a sampling rate of 200 MHz and 16 sampling channels. Eddy current signals are also used to acquire tip clearance signals, with a sampling rate of 5 MHz and 16 sampling channels. This generates 16 × 205 × 1,000,000 = 3,280,000,000 data points per second. If each sample is stored at 2 bytes, this would occupy approximately 12GB of storage per second. Clearly, using traditional storage methods, this processing and storage would be impossible within a single second.

[0058] The embodiments of the present disclosure provide a method for storing data of an aircraft engine blade, which is used for high-speed data processing and storage during the health monitoring of an aircraft engine blade.

[0059] See Figure 1 The aero-engine blade data storage method includes steps S101 to S104, and each step is described in detail below.

[0060] Step S101 : collecting signals from all blades of an aircraft engine through a plurality of sensors to obtain blade vibration signals and blade tip clearance signals corresponding to the sensors.

[0061] In this embodiment, multiple sensors are used to collect signals from all blades of the aircraft engine, and blade vibration signals and blade tip clearance signals of all blades corresponding to each sensor are obtained, wherein the blade vibration signals are digital signals and the blade tip clearance signals are analog signals.

[0062] Step S102 : generating health characteristic parameters corresponding to each sensor according to the blade vibration signal and the blade tip clearance signal corresponding to each sensor, and generating signal auxiliary information corresponding to each sensor according to each health characteristic parameter.

[0063] In this embodiment, the blade vibration signal and the tip clearance signal corresponding to each sensor are preprocessed to generate health characteristic parameters corresponding to each sensor, and further, signal ancillary information corresponding to each sensor is generated based on each health characteristic parameter.

[0064] Among them, the health characteristic parameters are indicators that can reflect the health status of the aircraft engine, which may include edge timestamps (rising edge x1, falling edge x2), tip clearance signal frequency F, and equally spaced sampling voltage amplitudes {v1, v2, v3…v N}, the health characteristic parameters are {x1,x2,F,{v1,v2,v3…v N The signal ancillary information is used to help restore the complete data information in the subsequent data readback, including the sampling rate Sa, data storage format Form, acquisition channel number Ch, sampling point timestamps {T1, T2, T3…T N} and its sampling point number N, blade tip signal characteristic value Btip, etc., the data frame of the signal auxiliary information is recorded as {Sa,Form,Ch,{T1,T2,T3…T N},N,Btip}.

[0065] Please note that, see Figure 2 It can be found that the digital signal generated by the blade vibration is only 0 and 1, so only the timestamps of the rising edge and the falling edge need to be stored to fully retain all the vibration information and remove redundant data; and for the tip clearance signal, it can be found that the analog signal generated by each blade is similar, so when storing data, each blade only needs to store N data points to fully reflect the changes in the tip clearance.

[0066] For example, in the actual monitoring process, N can be selected according to the actual working conditions. In this embodiment, N=5 is set. During the storage process, the extracted information of a blade is a complete data packet, that is, the minimum unit of stored data is the complete health characteristic parameter information of a blade, such as Figure 3 shown.

[0067] The vibration signal of each blade only stores the rising edge timestamp x1 and the falling edge timestamp x2; the tip clearance signal only extracts the five voltage values V1, V2, V3, V4, V5 near the tip of the blade and the corresponding timestamps T1, T2, T3, T4, T5 and signal frequency F; the same processing is performed on each blade in each channel to obtain the health characteristic parameters of the blade.

[0068] The auxiliary information generation module is designed in the Field-Programmable Gate Array (FPGA) to record the sampling rate Sa, data format Form, acquisition channel number Ch, the sampling point timestamps {T1, T2, T3, T4, T5} of each blade voltage amplitude and the number of sampling points N = 5, and the blade tip signal characteristic value Btip = V3. The arrangement format of a frame of data in the memory is as follows: Figure 4 As shown in the figure above.

[0069] In this embodiment, 16 channels are used to collect blade vibration signals and blade tip clearance signals respectively. In one frame of data, there are 18 parameters in total. Each data uses 8 bytes of space for storage, that is, Form = 8, so the size of each frame of data is 144 bytes; the digital signal sampling rate is 200MHz, and the analog signal sampling rate is 5MHz. The high 4 bytes of Sa store the digital sampling rate, and the low 4 bytes store the analog sampling rate. The data of different channels are arranged in the memory as follows Figure 4 As shown in the figure below, time-division multiplexing is used to distinguish data from different channels based on the Ch value. Data_CH1, Data_CH2, and Data_CHn in the figure all represent a complete frame of data. n is the number of analog channels. In this embodiment, n=16.

[0070] In a specific embodiment, step S102 includes: for each of the sensors, performing sliding window filtering on the tip clearance signal to obtain a filtered tip clearance signal; performing equally spaced voltage amplitude extraction on the filtered tip clearance signal to obtain the equally spaced sampled voltage amplitude; and taking the maximum value of all equally spaced sampled voltage amplitudes of each circle of each blade as the tip signal characteristic value.

[0071] In this embodiment, for one sensor, a tip clearance signal corresponding to the sensor is subjected to sliding window filtering to obtain a filtered tip clearance signal, thereby filtering out noise.

[0072] Furthermore, if the voltage corresponding to the tip clearance signal begins to drop, the tip clearance value that actually needs to be stored is obtained at intervals of a constant voltage value to obtain equally spaced sampling voltage amplitudes.

[0073] Furthermore, the maximum value of all equally spaced voltage amplitudes sampled in each circle of each blade is taken as the blade tip signal characteristic value.

[0074] Step S103 : determining the time buffer granularity corresponding to each sensor according to the attached information of each signal, and allocating a continuous address buffer area corresponding to each sensor.

[0075] In this embodiment, to achieve efficient storage and real-time processing of multi-sensor data, the temporal cache granularity is dynamically determined based on signal-attached information, and a continuous address cache is allocated. This temporal cache granularity balances storage efficiency and real-time performance, preventing cache overflows and data loss. Furthermore, address mapping within the continuous address cache optimizes data read and write efficiency and reduces memory fragmentation.

[0076] See Figure 5 In a specific embodiment, step S103 includes steps S1031 to S1033, and each step is described in detail below.

[0077] Step S1031 : For each of the sensors, calculate the characteristic value change rate according to the blade tip signal characteristic value.

[0078] In this embodiment, for each sensor, the characteristic value change rate is calculated based on the characteristic value of the blade tip signal. The characteristic value change rate is used to measure the speed at which the blade health characteristic parameter changes over time.

[0079] In a specific embodiment, step S1031 includes: calculating the absolute value of the difference between the blade tip signal characteristic value at the current circle timestamp and the blade tip signal characteristic value at the previous circle timestamp; calculating the difference between the current circle timestamp and the previous circle timestamp as the interval time; calculating the quotient of the absolute value of the difference and the interval time as the characteristic value change rate.

[0080] In this embodiment, the absolute value of the difference between the blade tip signal characteristic value at the current timestamp and the blade tip signal characteristic value at the previous timestamp is calculated; the difference between the current timestamp and the previous timestamp is further calculated as the interval time Δt; and the quotient of the absolute value of the difference and the interval time ΔV is further calculated as the characteristic value change rate. The specific calculation formula is the change rate

[0081] Step S1032: determining a change rate grading index according to the characteristic value change rate.

[0082] In this embodiment, the characteristic value change rate is normalized based on the dynamic range to determine the change rate classification index R rel .

[0083] In a specific embodiment, step S1032 includes: calculating the range of all equally spaced voltage amplitudes sampled at the current time stamp and all equally spaced voltage amplitudes sampled at the previous time stamp; and calculating the quotient of the characteristic value change rate and the range as the change rate grading index.

[0084] In this embodiment, the range difference ΔV of all equally spaced voltage amplitudes sampled at the current time stamp and the previous time stamp is calculated; the quotient of the characteristic value change rate and the range difference ΔV is calculated as the change rate classification index R rel The specific calculation formula is:

[0085] Step S1033 , classifying the characteristic value change rate according to a preset classification threshold and the change rate classification index, determining the time cache granularity according to the classification result, and allocating the continuous address cache area.

[0086] In this embodiment, the characteristic value change rate is classified based on a comparison between a preset classification threshold and a change rate classification index. The classification results are then used to determine the time cache granularity and allocate continuous address cache areas. This allows for hierarchical storage based on characteristic value change rates, balancing data integrity and storage load.

[0087] In a specific embodiment, the preset grading threshold includes a first grading threshold and a second grading threshold, and step S1033 includes: if the change rate grading index is greater than or equal to the first grading threshold, determining the time cache granularity to be the first time granularity, and allocating the continuous address cache area to the first cache area; the first cache area is used to store the signal ancillary information and the health characteristic parameters; if the change rate grading index is greater than or equal to the second grading threshold, and less than or equal to the first grading threshold, determining the time cache granularity to be the second time granularity, and allocating the continuous address cache area to the second cache area; the second cache area is used to store the tip clearance signal, the signal ancillary information and the health characteristic parameters; if the change rate grading index is less than or equal to the second grading threshold, determining the time cache granularity to be the third time granularity, and allocating the continuous address cache area to the third cache area; the third cache area is used to store the blade vibration signal and the tip clearance signal; wherein, the third time granularity, the second time granularity and the first time granularity decrease in sequence.

[0088] In this embodiment, if the change rate classification index R rel≥ the first classification threshold. When the DDR5 protocol of the PCIe4.0 bus protocol is used, the maximum data transmission delay time is 20 microseconds. It is determined that the internal working condition of the aircraft engine is in a state of drastic change at this time. The cache time granularity can be set to the first time granularity, and the first time granularity can be 1500 times to 3000 times the bus data transmission delay time. The continuous address cache area is allocated as the first cache area, and only the signal auxiliary information and the health characteristic parameters of the blade are stored. That is, the stored data at this time is: {{Sa,Form,Ch,{T1,T2,T3…T N},N,Btip},{x1,x2,F,{v1,v2,v3…v N}}}, each data occupies 8 bytes of space. The first classification threshold may be 50%.

[0089] For example, the first time granularity is 30ms, the corresponding DDR5 cache space (first cache area) is 1.6GB, and one frame of data is 144Byte. Then, this DDR5 buffer can cache 1.6GB / 144Byte=11650 frames of data. In this embodiment, the aircraft engine runs at a speed of 35,000 rpm and has 45 blades. Then, 35,000 / 60×45=26,250 frames of data can be generated per second. Because the cache storage is triggered every 30ms, the data cached in the DDR5 at a time is 26,250 / 1000×30=788 frames of data. The size of the DDR5 buffer fully meets the cache requirements.

[0090] If the second classification threshold ≤ the change rate classification index R rel ≤ the first classification threshold, it is determined that the aircraft engine is in a typical transition state at this time, and the cache time granularity is set to the second time granularity, which can be 3000 times to 4500 times the bus data transmission delay time. A continuous address cache area is allocated as the second cache area to store the blade health characteristic parameters, signal ancillary information, and blade tip clearance signal. That is, the stored data at this time is: {{Sa,Form,Ch,{T1,T2,T3…T N},N,Btip},{x1,x2,F,{v1,v2,v3…v N In this case, each data point of the health characteristic parameter and the signal ancillary information occupies 8 bytes of space, and each sampling point in the tip clearance signal occupies 2 bytes of space. The second classification threshold may be 10%.

[0091] If the change rate grading index R relIf the value is less than or equal to the second classification threshold, the aircraft engine is considered to be operating smoothly. The cache time granularity is set to the third time granularity, which can be at least 4500 times the bus data transmission delay. The cache stores the complete signal data of all channels, namely, only the blade vibration signal and the tip clearance signal, and no longer stores the blade health characteristic parameters or signal ancillary information. The stored data at this time is: {blade vibration signal, tip clearance signal}. Each sampling point of the blade vibration signal occupies 1 bit of space, and each sampling point of the tip clearance signal occupies 2 bytes of space.

[0092] Step S104: storing a target signal set corresponding to each sensor according to each time cache granularity and each continuous address cache area, wherein the target signal set includes at least two of the blade vibration signal, the tip clearance signal, the health characteristic parameter, and the signal ancillary information.

[0093] In this embodiment, DDR5 memory buffers are allocated to each sensor based on the continuous address buffers. The target signal set is written to the DDR5 memory buffers based on the time buffer granularity. Storage partitions are allocated on the solid-state drive, and data written to the DDR5 memory buffers is written to the storage partitions. This "FPGA + DDR5" approach replaces the traditional high-speed acquisition "CPU + DMA" approach. The CPU is not involved in the entire acquisition, processing, and storage process, eliminating CPU resource usage and freeing up more computing resources.

[0094] For example, if the rate of change index R rel ≥ the first classification threshold, the target data set includes signal ancillary information and health characteristic parameters; if the second classification threshold ≤ the change rate classification index R rel ≤ the first classification threshold, the target data set includes health characteristic parameters, signal ancillary information, and blade tip clearance signal; if the change rate classification index R rel ≤ the second classification threshold, then the target data set includes blade vibration signals and blade tip clearance signals.

[0095] See Figure 6 ,The storage process is as follows: ,Based on the dynamically adjusted cache time granularity and the different bandwidth requirements of ,each channel of data, after allocating a continuous address cache area in the DDR5 memory, ,then write the corresponding target data set into the continuous address cache area in parallel; ,the address of the allocated continuous address cache area is mapped to the FPGA’s Direct Memory Access (DMA) ,controller for subsequent efficient parallel writing of data.

[0096] Furthermore, based on the parallel synchronous cache mechanism and NVMe instructions, the data in the continuous address cache area is written in parallel to the storage partition of the NVMe SSD solid-state drive through FPGA, and the file system index is updated in real time.

[0097] Specifically, the continuous address cache area is divided into two sub-areas with read-write separation, and a parallel synchronous cache mechanism is used to achieve continuous data writing; continuous address write instructions are generated based on the NVMe protocol, and the cache area data is written in parallel to the solid-state drive storage partition through FPGA; the file system index is updated according to the write data of the solid-state drive storage partition.

[0098] The aircraft engine blade data storage method proposed in this embodiment uses multiple sensors to collect signals from all aircraft engine blades, obtaining blade vibration signals and tip clearance signals corresponding to each sensor. Based on the blade vibration signals and tip clearance signals corresponding to each sensor, health characteristic parameters corresponding to each sensor are generated, and signal ancillary information corresponding to each sensor is generated based on each health characteristic parameter. Based on each signal ancillary information, a time buffer granularity corresponding to each sensor is determined, and a continuous address buffer area corresponding to each sensor is allocated. A target signal set corresponding to each sensor is stored based on each time buffer granularity and each continuous address buffer area. The target signal set includes at least two of the blade vibration signal, the tip clearance signal, the health characteristic parameters, and the signal ancillary information. In this way, the blade vibration signals and tip clearance signals collected by each sensor are preprocessed to obtain health characteristic parameters and signal ancillary information. The signal ancillary information is then used to set a time buffer granularity and a continuous address buffer area for each sensor's signal, achieving efficient, low-redundancy storage with high real-time performance and flexible expansion.

[0099] Example 2

[0100] In addition, the present disclosure provides an aircraft engine blade data storage device 700, see Figure 7 ,include:

[0101] The acquisition module 701 is configured to acquire signals from all blades of the aircraft engine through a plurality of sensors, and obtain blade vibration signals and blade tip clearance signals corresponding to the sensors;

[0102] a processing module 702 for generating health characteristic parameters corresponding to each sensor based on the blade vibration signal and the blade tip clearance signal corresponding to each sensor, and generating signal auxiliary information corresponding to each sensor based on each health characteristic parameter;

[0103] a determination module 703, configured to determine a time buffer granularity corresponding to each of the sensors according to the attached information of each signal, and to allocate a continuous address buffer area corresponding to each of the sensors;

[0104] The storage module 704 is used to store the target signal set corresponding to each of the sensors according to each of the time cache granularities and each of the continuous address cache areas, wherein the target signal set includes at least two of the blade vibration signal, the blade tip clearance signal, the health characteristic parameter and the signal ancillary information.

[0105] Optionally, the health characteristic parameters include equally spaced sampled voltage amplitudes, and the signal ancillary information includes blade tip signal characteristic values; the processing module 702 is further used to perform sliding window filtering on the blade tip clearance signal for each of the sensors to obtain a filtered blade tip clearance signal; perform equally spaced voltage amplitude extraction on the filtered blade tip clearance signal to obtain the equally spaced sampled voltage amplitudes; and take the maximum value of all equally spaced sampled voltage amplitudes of each circle of each blade as the blade tip signal characteristic value.

[0106] Optionally, the determination module 703 is also used to calculate the characteristic value change rate of each sensor based on the characteristic value of the blade tip signal; determine the change rate grading index based on the characteristic value change rate; grade the characteristic value change rate according to a preset grading threshold and the change rate grading index, determine the time cache granularity based on the grading result, and allocate the continuous address cache area.

[0107] Optionally, the determination module 703 is also used to calculate the absolute value of the difference between the blade tip signal characteristic value at the current circle timestamp and the blade tip signal characteristic value at the previous circle timestamp; calculate the difference between the current circle timestamp and the previous circle timestamp as the interval time; calculate the quotient of the absolute value of the difference and the interval time as the characteristic value change rate.

[0108] Optionally, the determination module 703 is further used to calculate the range of all equally spaced voltage amplitudes sampled at the current circle timestamp and all equally spaced voltage amplitudes sampled at the previous circle timestamp; and calculate the quotient of the characteristic value change rate and the range as the change rate grading index.

[0109] Optionally, the preset grading threshold includes a first grading threshold and a second grading threshold, and the determination module 703 is also used to determine that the time cache granularity is the first time granularity if the change rate grading index is greater than or equal to the first grading threshold, and allocate the continuous address cache area as the first cache area; the first cache area is used to store the signal ancillary information and the health characteristic parameters; if the change rate grading index is greater than or equal to the second grading threshold, and less than or equal to the first grading threshold, the time cache granularity is determined to be the second time granularity, and the continuous address cache area is allocated as the second cache area; the second cache area is used to store the tip clearance signal, the signal ancillary information and the health characteristic parameters; if the change rate grading index is less than or equal to the second grading threshold, the time cache granularity is determined to be the third time granularity, and the continuous address cache area is allocated as the third cache area; the third cache area is used to store the blade vibration signal and the tip clearance signal; wherein, the third time granularity, the second time granularity and the first time granularity decrease in sequence.

[0110] Optionally, the health characteristic parameters include edge timestamps and tip clearance signal frequencies, and the signal ancillary information includes sampling rate, data storage format, acquisition channel number, sampling point timestamps of the equally spaced sampling voltage amplitudes, and the number of sampling points.

[0111] The device provided in the embodiment of the present disclosure can execute the steps of the aircraft engine blade data storage method provided in Example 1, which will not be described again to avoid repetition.

[0112] The aircraft engine blade data storage device proposed in this embodiment uses multiple sensors to collect signals from all aircraft engine blades, obtaining blade vibration signals and tip clearance signals corresponding to each sensor. Based on the blade vibration signals and tip clearance signals corresponding to each sensor, a health characteristic parameter corresponding to each sensor is generated, and signal ancillary information corresponding to each sensor is generated based on each health characteristic parameter. Based on each signal ancillary information, a time buffer granularity corresponding to each sensor is determined, and a continuous address buffer area is allocated to each sensor. A target signal set corresponding to each sensor is stored based on each time buffer granularity and each continuous address buffer area. The target signal set includes at least two of the blade vibration signal, the tip clearance signal, the health characteristic parameter, and the signal ancillary information. In this way, the blade vibration signals and tip clearance signals collected by each sensor are preprocessed to obtain the health characteristic parameters and signal ancillary information. The signal ancillary information is then used to set a time buffer granularity and a continuous address buffer area for each sensor's signal, achieving efficient, low-redundancy storage with high real-time performance and flexible expansion.

[0113] Example 3

[0114] In addition, an embodiment of the present disclosure provides a computer device, including a memory and a processor, wherein the memory stores a computer program, and when the computer program is executed by the processor, the method for storing aircraft engine blade data described in Example 1 is implemented.

[0115] The device provided in the embodiment of the present disclosure can execute the steps of the aircraft engine blade data storage method provided in Example 1, which will not be described again to avoid repetition.

[0116] Example 4

[0117] An embodiment of the present disclosure provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, the method for storing data of aircraft engine blades described in Embodiment 1 is implemented.

[0118] In this embodiment, the computer-readable storage medium may be a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk.

[0119] The computer-readable storage medium provided in this embodiment can implement the aviation engine blade data storage method provided in Example 1. To avoid repetition, it will not be described here.

[0120] In all examples shown and described herein, any specific values should be interpreted as merely exemplary and not limiting, and thus other examples of the exemplary embodiments may have different values.

[0121] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0122] The above-described embodiments merely illustrate several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that variations and modifications are possible without departing from the scope of the present invention, and such variations and modifications are fully within the scope of protection of the present invention.

Claims

1. A method for storing data of an aircraft engine blade, characterized in that: include: The signals of all blades of the aircraft engine are collected by multiple sensors respectively, and the blade vibration signals and blade tip clearance signals corresponding to the sensors are obtained; generating health characteristic parameters corresponding to each sensor according to the blade vibration signals and blade tip clearance signals corresponding to each sensor, and generating signal auxiliary information corresponding to each sensor according to each health characteristic parameter; Determining a time buffer granularity corresponding to each of the sensors according to the attached information of each signal, and allocating a continuous address buffer area corresponding to each of the sensors; The target signal set corresponding to each sensor is stored according to each time cache granularity and each continuous address cache area, and the target signal set includes at least two of the blade vibration signal, the blade tip clearance signal, the health characteristic parameter and the signal auxiliary information.

2. The method for storing data of an aircraft engine blade according to claim 1, characterized in that: The health characteristic parameters include equally spaced sampling voltage amplitudes, and the signal ancillary information includes blade tip signal characteristic values; Generating health characteristic parameters corresponding to each sensor according to the blade vibration signal and the blade tip clearance signal corresponding to each sensor, and generating signal auxiliary information corresponding to each sensor according to each health characteristic parameter, includes: For each of the sensors, performing sliding window filtering on the blade tip clearance signal to obtain a filtered blade tip clearance signal; Performing equal-interval voltage amplitude extraction on the filtered tip clearance signal to obtain the equal-interval sampling voltage amplitude; The maximum value of all equally spaced sampled voltage amplitudes of each blade in each circle is taken as the blade tip signal characteristic value.

3. The method for storing data of an aircraft engine blade according to claim 2, characterized in that: The determining of the time buffer granularity corresponding to each sensor according to the auxiliary information of each signal, and allocating a continuous address buffer area corresponding to each sensor, includes: For each of the sensors, calculating a characteristic value change rate according to the blade tip signal characteristic value; Determining a change rate grading index according to the characteristic value change rate; The characteristic value change rate is graded according to a preset classification threshold and the change rate classification index, the time cache granularity is determined according to the classification result, and the continuous address cache area is allocated.

4. The method for storing data of an aircraft engine blade according to claim 3, characterized in that: Calculating the characteristic value change rate according to the blade tip signal characteristic value includes: Calculate the absolute value of the difference between the blade tip signal characteristic value at the current circle timestamp and the blade tip signal characteristic value at the previous circle timestamp; Calculate the difference between the current circle timestamp and the previous circle timestamp as the interval time; The quotient of the absolute value of the difference and the interval time is calculated as the characteristic value change rate.

5. The method for storing data of aircraft engine blades according to claim 3, characterized in that: Determining a change rate grading index according to the characteristic value change rate includes: Calculate the range of all equally spaced voltage amplitudes sampled at the current timestamp and the range of all equally spaced voltage amplitudes sampled at the previous timestamp; The quotient of the characteristic value change rate and the range is calculated as the change rate grading index.

6. The method for storing data of aircraft engine blades according to claim 3, characterized in that: The preset classification threshold includes a first classification threshold and a second classification threshold, and the grading of the characteristic value change rate according to the preset classification threshold and the change rate classification index, determining the time cache granularity according to the grading result, and allocating the continuous address cache area include: If the change rate classification index is greater than or equal to the first classification threshold, determining the time cache granularity to be the first time granularity, and allocating the continuous address cache area as the first cache area; the first cache area is used to store the signal auxiliary information and the health characteristic parameter; If the change rate classification index is greater than or equal to the second classification threshold and less than or equal to the first classification threshold, determining the time cache granularity to be the second time granularity and allocating the continuous address cache area as the second cache area; the second cache area is used to store the tip clearance signal, the signal ancillary information, and the health characteristic parameter; If the change rate classification index is less than or equal to the second classification threshold, determining the time cache granularity to be a third time granularity and allocating the continuous address cache area to be a third cache area; the third cache area is used to store the blade vibration signal and the blade tip clearance signal; The third time granularity, the second time granularity and the first time granularity decrease in sequence.

7. The method for storing data of an aircraft engine blade according to claim 1, characterized in that: The health characteristic parameters include edge timestamps and blade tip clearance signal frequencies, and the signal ancillary information includes sampling rate, data storage format, acquisition channel number, sampling point timestamps of the equally spaced sampling voltage amplitudes, and the number of sampling points.

8. An aircraft engine blade data storage device, characterized in that: include: An acquisition module is used to respectively acquire signals from all blades of the aircraft engine through multiple sensors to obtain blade vibration signals and blade tip clearance signals corresponding to each of the sensors; a processing module, configured to generate health characteristic parameters corresponding to each of the sensors based on the blade vibration signals and blade tip clearance signals corresponding to each of the sensors, and to generate signal ancillary information corresponding to each of the sensors based on each of the health characteristic parameters; a determination module, configured to determine a time buffer granularity corresponding to each of the sensors according to the attached information of each signal, and to allocate a continuous address buffer area corresponding to each of the sensors; A storage module is used to store the target signal set corresponding to each of the sensors according to each of the time cache granularities and each of the continuous address cache areas, wherein the target signal set includes at least two of the blade vibration signal, the tip clearance signal, the health characteristic parameter and the signal ancillary information.

9. A computer device, characterized in that: The method comprises a memory and a processor, wherein the memory stores a computer program, and when the computer program is executed by the processor, the method for storing data of an aircraft engine blade according to any one of claims 1 to 7 is implemented.

10. A computer-readable storage medium, characterized in that It stores a computer program, which, when executed by a processor, implements the aviation engine blade data storage method according to any one of claims 1 to 7.

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