• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A method (100) for controlling parts for multi-rotating machine machines rotated at different rotational speeds, the method (100) comprising sampling (102) of data provided by the vibration sensor at a frequency of sampling at least as large as the largest rotational speed of the plurality of rotating members to form a data set, and determining (104) an actual rotational frequency for at least some of the rotational elements during the sampling of data.
    公开号:FR3025886A1
    申请号:FR1558610
    申请日:2015-09-15
    公开日:2016-03-18
    发明作者:Steven Bonnett；Timothy Robert North；Tod Alexander Gilbert
    申请人:GE Aviation Systems Ltd；
    IPC主号:
    专利说明:

    [0001] 1 PARTS CONTROL SYSTEM AND METHOD Vibration data can be acquired for a machine, including an aircraft, and personnel can then seek to identify and correct potential problems from the vibration data. In the prior art, vibration data has been acquired piece by piece using sampling rates to target specific speed parts. In this way, the data is acquired multiple times using a single sensor for each of the parts. In a first embodiment, the invention relates to a coin control method for machines comprising multiple rotating members, which are rotated at different speeds of rotation, and at least one vibration sensor, the method comprising sampling data provided by the vibration sensor at a sampling frequency sufficient to control a largest rotational speed of the plurality of rotating members to form a data set, determining a true rotational frequency for a least some of the rotating elements during data sampling, and producing a virtual vibration signal from the data set for at least some of the rotating elements by filtering the data set against a frequency sample to control the rotating element / each of the rotating elements.
    [0002] In another embodiment, the invention relates to a system having rotary multi-rotating machines which are rotated at different rotational speeds, a vibration sensor adapted to measure the rotational speed of one of the rotational machines. multiple rotary members and a processor cooperating with the vibration sensor and a tachometer for receiving information therefrom and adapted to sample data at a sampling frequency sufficient to control the largest rotational speed of the plurality of rotating members to form a set of data, determine an actual rotational frequency for at least some of the rotational elements during data sampling and produce a virtual vibration signal from the data set for at least some of the elements rotating by filtering the data set against a frequency sample to control at least some of the rotating elements. The invention will be better understood on studying the detailed description of an embodiment taken by way of nonlimiting example and illustrated by the appended drawings in which: - Figure 1 is a schematic view of a rotorcraft in which embodiments of the invention can be implemented; FIG. 2 is a diagrammatic representation of multiple rotating elements and sensors that can be part of the rotorcraft of FIG. 1; FIG. 3 represents examples of data signals that can be produced; and FIG. 4 is a flowchart illustrating a part control method according to one embodiment of the invention. FIG. 1 schematically represents a system in the form of an aircraft, more specifically a rotorcraft 10, which can implement embodiments of the invention and can comprise rotating machines having multiple rotating elements, which are brought to rotate at different rotational speeds. More particularly, the rotorcraft 10 has been shown to comprise a propulsion system which comprises a gas turbine engine 12, a gearbox 14, a drive shaft 16, a transmission 18, a main rotor 20, a gearbox 22 anti-torque rotor, an anti-torque rotor drive shaft 24 with various support bearings 26 and an anti-torque rotor gearbox 28. The motor 12 drives the transmission 18 through the drive shaft 16, rotating the main rotor 20. Power is also generated by the transmission 18 to drive the rotor drive shaft 24. couple. One or more control mechanisms (not shown) may be included in the rotorcraft 10 and may be actuated by a pilot to operate the rotorcraft 10. Although a rotorcraft has been shown, the system comprising the multiple rotatable members may be be any suitable system, including another vehicle, a wind turbine or an engine. In order to determine the vibration data, a vibration sensor 30 is part of the system. The vibration sensor 30 may be designed to measure the vibrations of the multiple rotating members. The vibration sensor 30 may be satisfactorily located in any part of the rotorcraft 10 where there are rotating elements to be monitored. A tachometer 32 may also be in the rotorcraft 10 and may be adapted to measure the rotational speed of one of the plurality of rotating members. For example, the tachometer 32 may measure the rotational speed of one of the pinions of the anti-torque rotor gearbox 22. Again, the tachometer 32 may be located in a satisfactory manner in the immediate vicinity of any of the rotating elements present in the rotorcraft 10. An automaton 40 can cooperate with the vibration sensor 30 and the tachometer 32 so as to be able to receive from them information. The controller 40 may also be connected to other members and systems of the rotorcraft 10, including other controllers of the rotorcraft 10. The controller 40 may comprise a memory 42, the memory may comprise a random access memory (RAM), a ROM, a flash memory or one or more different types of portable electronic memory such as disks, DVDs, CD-ROMs, etc. or any appropriate combination of these types of memory. The memory 42 may contain information relating to the rotorcraft 10, including reference values for the rotary elements present therein.
    [0003] The controller 40 may include one or more processors 44, which may execute any suitable programs. The controller 40 may understand and cooperate with any number of software or instructions designed to implement the various processes, process tasks, calculations, and control / display functions necessary for the operation of the rotorcraft 10. The controller 40 is shown communicating with the members and systems including the motor 12 and it is contemplated that the controller 40 may contribute to the operation of the rotorcraft and receive information from the members and systems. The controller 40 may be part of a flight management system or may cooperate with the flight management system. The controller 40 can also cooperate with a flight screen 46 so that information can be displayed to the attention of a pilot of the rotorcraft 10. Although the description has hitherto focused on the processor present in the rotorcraft 10, it is contemplated that parts of the embodiments of the invention may be implemented anywhere, particularly in a processor or computer located in a ground system, which may communicate with the rotorcraft 10 by any suitable communication link. This processor in the ground system may be considered part of the system, even if it is remote from the rotorcraft 10. A communication module 48 may be present in the rotorcraft 10 to transmit various data of the rotorcraft 10 to that processor. on the ground. For example, it is contemplated that the data provided by the vibration sensor 30 and the tachometer 32 may be sent to a ground processor via the communication module 48. Alternatively, the controller 40 may process these data. The communication module 48 can lend itself to radio links with other systems and devices by means of packet radio communication, a link and the transmission of the information processed via the communication module 48. satellite, wireless fidelity (WiFi), WiMax, Bluetooth, ZigBee, a 3G radio signal, a code division multiple access radio (CDMA) signal, a mobile special group (GSM), a 4G radio signal, a long term evolution signal (LTE), an Ethernet or any combination thereof. In addition, the particular type or mode of wired or wireless communication is not essential for the embodiments of the present invention, and radio networks developed in the future will undoubtedly come within the scope of the present invention. embodiment of the invention.
    [0004] For ease of explanation, the remainder of the description will relate to the operation of the controller 40, although it will be understood that a remote processor may also be used. The controller 40 may comprise all or part of a computer program having a set of executable instructions for the control of parts. The program 10 may include a computer program that may include computer-readable media for holding computer executable instructions or data structures in which computer executable instructions or data structures are stored. These computer-readable media may be any existing media, which is accessible to a versatile or specific computer or other processor machine. Overall, such a computer program may include routines, programs, objects, components, data structures, algorithms, and so on. which have the effect of performing particular tasks or of implementing particular abstract data types. Computer executable instructions, corresponding data structures and programs are examples of program codes for performing the information exchange described herein. The computer executable instructions may include, for example, instructions and data, which cause a general purpose computer, a particular computer, or a particular processing machine to perform a certain function or group of functions. For ease of explanation, FIG. 2 shows examples of rotating parts in the form of pinions 60, 62, 64 rotated at different speeds of rotation. During operation of the rotorcraft 10, the controller 40 may receive information from the vibration sensor 30 and the tachometer 32. It is contemplated that the data can be acquired during a steady flight regime of the rotorcraft 10 so that no other factor then influences the sensor data. The controller 40 may sample data provided by the vibration sensor 30 at a sampling frequency sufficient to control the largest rotational speed of the plurality of rotating members (i.e. the gears 60, 62, 64) to form a set of data. The controller may use the detected data provided by the tachometer 32 to determine an actual rotational frequency for the gears 60, 62, 64 during data sampling. More particularly, the tachometer 32 serves to identify a revolution of each piece. For example, the memory 42 of the controller 40 may contain the geometry of the parts, including the way the parts interact. From this information, the controller 40 can produce a virtual vibration signal from the data set for at least some of the rotational elements by filtering the data set at a sampling rate to control each of the data elements. In particular, a graph 70 of raw data is shown to include vibration data 72 and tachometer data 74. This data can be acquired at a maximum sampling rate to form the raw data. A filter may be applied to graph 70 of raw data to resample according to a given number of points per rotation for each speed of each of the rotating parts. For example, the graph 80 represents the resampled data for the pinion 60. The vibration data 82 has been resampled at an exemplary sampling rate of 4777 Hz and the modified tachometer data 84 for the pinion 60 are indicated. Conversely, graph 90 represents resampled data for pinion 64. Vibration data 92 has been resampled at an exemplary sampling rate of 2770 Hz and modified tachometer data 94 for pinion 64 are indicated. It has been determined that there is one or more relationships between the vibration sensors, such as accelerometers, and the rotating parts which they control and that the use of a filter makes it possible to produce signals such as they had been sampled at a reduced frequency. Thus, for each rotating part, the raw data can be resampled using a filter according to a common number of data points per revolution. Thus, the controller 40 may include a filter to produce the virtual vibration signals. The controller 40 may also employ a series of fixed replication filters at a given sampling rate for the raw data to produce the virtual vibration signals. According to yet another possibility, the controller 40 can use multiple sampling devices sampling at different frequencies the raw data provided by the same sensor.
    [0005] As noted above, the embodiments described herein may include a computer program comprising computer-readable media for holding computer executable instructions or data structures or in which computer executable instructions or structures are stored. of data. These computer-readable media may be any existing media accessible to a general-purpose or special computer or other processor machine. By way of example, such computer-readable media may comprise a RAM, ROM, EPROM, EEPROM, CD-ROM or other optical storage disk, magnetic storage disk or other magnetic storage devices, or any other medium that can be used to hold or store the desired program code in the form of computer executable instructions or data structures accessible to a general purpose or special computer or to another processor machine. When information is transmitted or provided over a network or other communication link (wired or both wired and wireless) to a machine, the machine appropriately perceives the connection as a computer-readable medium. Thus, any connection of this type is rightly called computer-readable medium. Combinations of the above means are also included in the definition of computer-readable media. The computer executable instructions include, for example, instructions and data, which may cause a general purpose computer, a particular computer, or particular processing machines to perform a certain function or group of functions.
    [0006] Embodiments will be described in the general context of steps of a method that may be implemented in one embodiment by a program containing computer executable instructions, including program codes, for example under the form of program modules run by computers in networked environments. Overall, the program modules include routines, programs, objects, components, data structures, and so on. which have the technical effect of performing particular tasks or of implementing particular abstract data types. Computer executable instructions, corresponding data structures and program modules are examples of program codes for performing steps of the method described herein. The particular order of these executable instructions or corresponding data structures are examples of corresponding acts to implement the functions described in these steps. Embodiments may also be implemented in distributed computing environments where tasks are performed by local and remote processing devices in connection (by cable links, radio links, or a combination of wired and wireless links). via a communication network. In a distributed computing environment, program modules may be located in local and remote storage devices. The above representation has only context value and the rotating machine system can include any additional appropriate room and be used in any suitable manner. In one embodiment of the invention, Figure 4 illustrates a method 100, which may be used for part control. The method 100 starts at 102 by sampling data from the vibration sensor 30 by a processor such as the controller 40, at a sampling frequency sufficient to control the largest rotational speed of the multiple rotating members of the rotorcraft 10 so that to form a data set. In the case of the rotorcraft 10 equipped with the gears 60, 62, 64, the vibration sensor 30 can detect vibrations emanating from these three rotating parts. At 104, an actual rotational frequency may be determined by the controller 40 for at least some of the rotating elements during the given sampling. More particularly, a detection signal can be received from the tachometer 32 and this information and the known arrangement of the gears 60, 62, 64, the number of times each of which rotates due to the rotation of the pinion 64, can be used to determine the actual rotational frequency of each of the gears 60, 62, 64. For example, the controller 40 may use the tachometer data 32 and the known part geometry to determine the relative speed of each individual part. It is envisaged that the actual rotational frequency of all the rotating elements can be determined for at least some or all of the rotating elements to be controlled.
    [0007] These data are then used to identify the individual rotations of each piece in the raw data. The desired resampling frequencies are derived from the rotational speed of the workpieces and the number of teeth, and the filter is applied to the raw signal over the lapse of time to produce the virtual signals at 106. Thus, virtual vibration signals can be generated from the data set for at least some of the rotating elements by filtering the data set at a sampling rate for at least some of the rotating elements. By way of non-limiting example, for a specific part, an exact resampling frequency can be chosen as a function of the desired number of samples per revolution of the part. By way of non-limiting examples, these resampling filters can generally be considered as interpolation or decimation filters according to whether they perform oversampling or subsampling. The high sampling rate obtained as explained above may be subsampled at a lower sampling rate. There may be cases where it may be desirable to intercept a specific number of samples per tooth of a fast-rotating, multi-toothed pinion. In this case, the raw data may be over-sampled. It is also envisioned that a decimation filter such as a fixed ratio filter may be used in combination with an interpolation filter and that this combination may be considered as filtering the data set at a frequency of sampling to control each or at least some of the multiple rotating elements. This allows acquisition by the sensor to produce data on the condition of multiple parts at different rotational speeds. The filter can be applied to the data for resampling according to a given number of points per rotation for each speed of the rotational member. In this way, virtual vibration signals are produced for all of the rotating elements because the application of a filter enables the production of virtual signals as if they had been sampled at a different frequency, with a reduced frequency. The part control process is flexible and the illustrated process is for illustrative purposes only. For example, the sequence of steps shown is for illustrative purposes only and is not intended to limit process 100 in any way, it being understood that the steps may be in a different logical order or that Additional or intermediate steps may be included deviating from the embodiments of the invention. For example, in the case where the rotating machine is an aircraft, the method may start with the flight of the aircraft at a fixed flight regime during sampling. According to another non-limiting example, the method 100 may also include the fact that once the virtual vibration signals have been generated, one or more of these can be processed to determine a state of vibration. the machine. This may include the detection or prediction, by a processor, of a mechanical anomaly according to the determined vibrations of at least one rotating part. According to a non-limiting example, this may include the fact that the virtual signals can be compared with reference values. The reference values may be any appropriate values, including whether the reference values may include appropriate values or intervals defined by history for the rotating parts. For example, the reference value can be calculated from a history of the data provided by the sensor. Thus, the virtual signals can be compared with the results obtained in previous flights for the same aircraft and with respect to the entire aircraft fleet. Alternatively, the reference value may be stored in the memory 42 described above. The processing may include determining whether or not a virtual signal meets a predetermined threshold. In this way, the controller 40 and / or a computer on the ground can / can determine if the results of the comparison are admissible. The "respect" of the threshold here means that the comparison of the variation respects the predetermined threshold being in particular equal to, lower than or greater than the threshold value. This determination can easily be modified to be respected by a positive / negative comparison or a true / false comparison. For example, a value below the threshold can easily be met by applying a higher value than a test at the time of the digital inversion of the data. The controller 40 may also be designed to process the virtual vibration signals over time to determine drifts, trends, bearings or peaks in the vibration signals to predict abnormalities of the rotating machine. These anomalies in the data may be too subtle in a day-to-day comparison to make such predictions of anomalies.
    [0008] In practice, reference values and comparisons can be converted into an algorithm for controlling parts of the rotating machine. This algorithm can be converted into a computer program comprising a set of executable instructions, which can be executed by the controller 40 and / or another processor.
    [0009] It is also contemplated that the process or parts of the process can be repeated. For example, flight, sampling, determination, signal generation, and processing may be repeated after a predetermined number of flight hours. Yet another example of how the method 100 may differ is that the method may include the fact that the data set and the tachometer data can be transmitted from the rotorcraft so that another processor can produce the virtual signals of vibration. Alternatively, the generated virtual vibration signals can be transmitted from the aircraft so that a ground processor can process them. Furthermore, the method may also include providing an indication of any specified anomalies or predicted mechanical abnormalities. The indication may be produced in any suitable manner, at any convenient location, including on a display screen 46 on board the rotorcraft 10 and / or in the ground system. For example, this indication may include presenting an alarm to a user if a mechanical abnormality is detected. Advantageous effects of the embodiments described above include that data collected by a single sensor can be used to simultaneously acquire vibration data for a number of parts. This vibration control can be used to detect mechanical anomalies sufficiently in advance to allow preventative maintenance. In the prior art, vibration data was obtained piece by piece using variable sampling rates to target specific speed pieces, so data had to be acquired multiple times from the same sensor. .
    [0010] As a result, total acquisition times long enough to control the entire series of different rotating parts were required. Since these data acquisitions usually require the aircraft to maintain a stable flight regime (ie, a cruising speed of 100 knots), the aircraft is often required to perform specific flights by maintaining these regimes for a long time just to acquire these regimes. data. The embodiments described above allow the acquisition of vibration data at a high sampling rate at one time for all sensors. The embodiments described above allow the analysis of many pieces from a single set of raw data acquired. This reduces the time taken to acquire vibration data for each part while allowing a single vibration sensor to control different rotating parts. On the other hand, data on all necessary parts can be acquired multiple times in one go because the time required is greatly reduced. Acquiring information multiple times in one go increases the chances of detecting anomalies before they occur. With the embodiments described above, special flights for acquiring piece status data are much less likely to be required, which increases the availability of the aircraft and reduces costs. Insofar as this is not already described, the various features and structures of the various embodiments may, if desired, be used in combination with each other. The fact that a feature may not be illustrated in all of the embodiments should not be interpreted to mean that it can not be, this is only intended to make the description shorter. Thus, the various features of the various embodiments can be mixed and adapted to form new embodiments, whether or not the new embodiments are expressly described. All combinations or permutations of details described herein are covered by this disclosure. 5 10
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. A method (100) for controlling workpieces for machines having multiple rotating members (60, 62, 64) rotated at different speeds of rotation, and at least one vibration sensor (30), the method (100) comprising: sampling (102) data provided by the vibration sensor (30) at a sampling frequency sufficient to control a largest rotational speed of the plurality of rotating members (60, 62, 64) to form a set of data determining (104) an actual rotational frequency for at least some of the plurality of rotating elements (60, 62, 64) during data sampling; and generating (106) a virtual vibration signal from the data set for at least some of the plurality of rotating elements (60, 62, 64) by filtering the data set at a sampling rate to controlling said at least some of the plurality of rotating members (60, 62, 64).
    [0002]
    The method (100) of claim 1, wherein determining (104) the actual rotational frequency for said at least some of the plurality of rotatable members (60, 62, 64) includes determining the actual rotational frequency further one of the plurality of rotating members (60, 62, 64).
    [0003]
    The method (100) of claim 1 or 2, wherein virtual vibration signals are generated for all of the plurality of rotating members (60, 62, 64).
    [0004]
    A method (100) according to any one of the preceding claims, further comprising processing the virtual signal for said at least some plural rotating elements (60, 62, 64) to determine a state of the machine.
    [0005]
    The method (100) of claim 4, wherein the processing comprises detecting, by a processor (40), a mechanical defect 3025886 16 based upon determined vibrations of at least one rotatable member (60, 62). , 64).
    [0006]
    The method (100) of claim 5, further comprising presenting an alarm to a user when a mechanical abnormality is detected.
    [0007]
    The method (100) of any one of the preceding claims, wherein the machine is an aircraft (10).
    [0008]
    The method (100) of claim 7, further comprising the flight of the aircraft (10) at a fixed flight regime during sampling. 10
    [0009]
    The method (100) of claim 8, further comprising repeating the flight, sampling, determination, production and processing after a predetermined number of flight hours.
    [0010]
    The method (100) according to any one of claims 7 to 9, further comprising communicating the virtual vibration signals produced from the aircraft (10).
    [0011]
    A system, comprising: a rotating machine having multiple rotating members (60, 62, 64) rotated at different speeds of rotation; a vibration sensor (30) adapted to measure vibrations of the plural rotating members (60, 62, 64); a tachometer (32) for measuring the rotational speed of one of the plurality of rotating members (60, 62, 64); and a processor (40) cooperating with the vibration sensor (30) and the tachometer (32) to receive information therefrom and adapted to sample data provided by the vibration sensor (30) at a frequency of sufficient to monitor a largest rotational speed of the plurality of rotating members (60, 62, 64) to form a data set, to determine an actual rotational frequency for at least some of the plurality of rotatable members (60, 62, 64) during the sampling of the data and producing a virtual vibration signal from the data set for at least some of the plurality of rotating elements (60, 62, 64) by filtering the data set following a 3025886 17 sampling frequency for controlling said at least some multiple rotating elements (60, 62, 64).
    [0012]
    The system of claim 11, further comprising a communication module (48) for transmitting the generated signals. 5
    [0013]
    13. System according to claim 11 or 12, wherein the rotating machine is a gearbox (14).
    [0014]
    The system of any one of claims 11 to 13, wherein the processor (40) is further adapted to process the virtual signals to determine a state of the rotating machine. 10
    [0015]
    The system of any one of claims 11 to 14, wherein the processor (40) comprises a filter for producing the virtual vibration signals.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3025886B1|2019-07-19|SYSTEM AND METHOD FOR CONTROLLING PARTS
    CA2813556C|2019-01-15|System for monitoring an engine test bed
    EP2376988B1|2013-07-10|Standardisation of data used for monitoring an aircraft engine
    EP2912526B1|2017-12-06|System for monitoring a set of components of a device
    EP2807460B1|2021-05-05|System to acquire the vibration signal of a rotating motor
    EP3658881B1|2021-07-07|Method and device for searching for a defect capable of affecting a rotating mechanical power transmission device
    WO2015086959A1|2015-06-18|Method and device for detecting mechanical faults in a variable speed rotating machine
    FR2987443A1|2013-08-30|DEVICE FOR DETECTING ANOMALIES BY ACOUSTIC ANALYSIS OF AN AIRCRAFT TURBOMACHINE
    FR2905763A1|2008-03-14|METHOD AND SYSTEM FOR DIAGNOSING AN AIRCRAFT FROM MEASUREMENTS CARRIED OUT ON THE AIRCRAFT.
    FR3025337B1|2019-08-16|SYSTEM FOR CREATING AND DEPLOYING A MODEL OF INFERENCE
    FR3051926A1|2017-12-01|AIRCRAFT COMPONENT CONTROL SYSTEM
    CA3028050C|2020-05-12|Monitoring and detection process for the formation of a degradation in at least one mobile part in a rotating mechanism and associated system
    FR3035232A1|2016-10-21|SYSTEM FOR MONITORING THE HEALTH CONDITION OF AN ENGINE AND ASSOCIATED CONFIGURATION METHOD
    EP3215897B1|2020-07-08|Improved state controller for a system driven by a command
    FR3011115A1|2015-03-27|PARAMETER DISPLAY METHOD
    FR3015670A1|2015-06-26|DEVICE FOR DETECTING FAILURE PREMIUMS OF A MECHANICAL SYSTEM
    EP3923104A1|2021-12-15|Method and system for controlling a damage level of at least one part of an aircraft, associated aircraft
    EP3913348A1|2021-11-24|System and method for monitoring the wear of a free wheel and associated device
    EP3785006B1|2021-11-24|Method and device for monitoring a gear system
    EP2784616A1|2014-10-01|Method for detecting and acknowledging an abrupt change in at least one supervision indicator of a device
    EP3671583A1|2020-06-24|Method and device for storing digital data
    EP2541505A1|2013-01-02|Method for monitoring an aircraft by vibration acquisitions
    FR3090913A1|2020-06-26|CHARACTERIZATION METHOD OF A MOTION SIMULATOR, MONITORING METHOD AND CORRESPONDING DEVICE
    WO2019145432A1|2019-08-01|Enhancing the performance of electronic devices
    FR3087241A1|2020-04-17|RELIABILITY ESTIMATE OF MECHANICAL PART
    同族专利:
    公开号 | 公开日
    FR3025886B1|2019-07-19|
    US20160076931A1|2016-03-17|
    GB2530093B|2017-02-01|
    GB201416252D0|2014-10-29|
    US9897479B2|2018-02-20|
    GB2530093A|2016-03-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JPH0125408B2|1978-02-22|1989-05-17|Hitachi Ltd|
    US4213114A|1979-03-07|1980-07-15|Vibro-Meter Sa|Vibration monitoring system for an aircraft engine|
    JPS6317167B2|1980-03-19|1988-04-12|Hitachi Ltd|
    US4408294A|1981-03-27|1983-10-04|General Electric Company|Method for on-line detection of incipient cracks in turbine-generator rotors|
    US5258923A|1987-07-22|1993-11-02|General Electric Company|System and method for detecting the occurrence, location and depth of cracks in turbine-generator rotors|
    US4872337A|1988-01-29|1989-10-10|Watts Robert J|Nondestructive testing of gears|
    US5445028A|1992-09-18|1995-08-29|Ametek Aerospace Products Inc.|Dynamic digital tracking filter|
    US6681634B2|2001-12-11|2004-01-27|Itt Manufacturing Enterprises, Inc.|Bearing defect detection using time synchronous averaging of an enveloped accelerometer signal|
    US7027953B2|2002-12-30|2006-04-11|Rsl Electronics Ltd.|Method and system for diagnostics and prognostics of a mechanical system|
    GB0308467D0|2003-04-11|2003-05-21|Rolls Royce Plc|Method and system for analysing tachometer and vibration data from an apparatus having one or more rotary components|
    US7912659B2|2004-06-28|2011-03-22|General Electric Company|System and method for monitoring the condition of a drive train|
    WO2006030786A1|2004-09-13|2006-03-23|Nsk Ltd.|Abnormality diagnosis device and abnormality diagnosis method|
    WO2010074648A1|2008-12-22|2010-07-01|S.P.M. Instrument Ab|An analysis system|
    FR2946387B1|2009-06-05|2011-07-08|Snecma|DEVICE AND METHOD FOR DETECTING A FAILURE OF A LOW PRESSURE FUEL PUMP OF A TURBOJET AND TURBOJET ENGINE WITH SAID DEVICE|
    US9651443B2|2014-06-06|2017-05-16|General Electric Company|System and method for protecting rotary machines|US20170067860A1|2015-09-03|2017-03-09|Paul Grabill|Control Area Network Machine Diagostic|
    US10379133B2|2016-01-20|2019-08-13|Simmonds Precision Products, Inc.|Speed estimation systems|
    CN113252929B|2021-07-05|2022-02-01|格创东智科技有限公司|Rotating speed determination method and device, electronic equipment and computer readable storage medium|
    法律状态:
    2016-09-26| PLFP| Fee payment|Year of fee payment: 2 |
    2017-09-25| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-01| PLSC| Search report ready|Effective date: 20180601 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    GB1416252.3A|GB2530093B|2014-09-15|2014-09-15|Assembly and method of component monitoring|
    GB1416252.3|2014-09-15|
    [返回顶部]