CN110821578B - Mass flight event identification method and identification system - Google Patents
Mass flight event identification method and identification system Download PDFInfo
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- CN110821578B CN110821578B CN201810921426.9A CN201810921426A CN110821578B CN 110821578 B CN110821578 B CN 110821578B CN 201810921426 A CN201810921426 A CN 201810921426A CN 110821578 B CN110821578 B CN 110821578B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
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Abstract
The invention relates to a mass flight-off event identification method and system for an aircraft engine. The identification method comprises the following steps: step a, identifying amplitude surge according to the fundamental frequency vibration signal; and b, judging the amplitude stability of the amplitude sudden increase section identified in the step a, and identifying a mass flying-off event. The identification method and the identification system have the advantages of high efficiency and accuracy in identification, simple system architecture, low cost and the like.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a method and a system for identifying a mass flight-off event of an aircraft engine.
Background
The rotary parts of the aircraft engine bear huge centrifugal force, the working environment is complex and severe, the rotary parts are subjected to the impact action of high-speed airflow and even subjected to extreme working conditions such as bird collision, ice swallowing and the like, and therefore the mass falling events of the rotary parts such as blade falling and the like are very likely to occur in the service process of the aircraft engine.
The flying-off of the fan blades of the aircraft engine is an extremely serious quality flying-off event of rotating parts, can cause the damage of the engine and even endanger the safety of the whole aircraft and the life of passengers, because the fan flying-off block has high energy and can penetrate through a casing, further endanger a control circuit, an aircraft oil circuit, an oil tank, a cabin and the like, once the equipment is damaged, the aircraft loses the operation and control, oil leakage and fire, and the aircraft is damaged and killed, thereby causing serious safety accidents.
In order to ensure stable and safe operation of the aircraft engine, the aircraft engine is generally provided with a vibration monitoring system to monitor the operation state. In order to avoid the increase of unbalanced force, vibration and the like caused by the mass loss of the rotating part, a mass runaway event needs to be monitored and identified, and once the mass runaway event occurs to the rotor, corresponding measures are taken in time so as to ensure the safety of the operation of the engine.
Disclosure of Invention
It is an object of the present invention to provide a method of identifying a mass fly-off event.
It is an object of the present invention to provide a system for identification of mass flight events.
According to one aspect of the invention, the method for identifying the mass flight-off event comprises the following steps:
step a, identifying amplitude surge according to the fundamental frequency vibration signal;
and b, judging the amplitude stability of the amplitude sudden increase section identified in the step a, and identifying a mass flying-off event.
In an embodiment of the identification method, the method further comprises:
in the step b, the rotating speed sudden increase is identified according to the rotating speed signal so as to eliminate the misjudgment caused by the rotating speed sudden increase.
In an embodiment of the identification method, the step of obtaining a fundamental frequency vibration signal in step a includes:
a0., acquiring the change of the fundamental frequency along with time according to the rotating speed signal, and designing a tracking filter taking the power frequency as the center frequency;
and step a01, filtering the vibration signal by adopting the tracking filter to obtain a fundamental frequency vibration signal.
In an embodiment of the identification method, the step of identifying the amplitude spikes in the step a includes:
step a1. dividing the fundamental frequency vibration signal into a plurality of signal segments with zeros;
a step a2, forming a signal long section by using N continuous signal small sections, wherein N is an integer greater than or equal to 2, so that the plurality of signal small sections form a plurality of signal long sections, and counting vibration amplitude characteristic parameter values in each signal long section;
step a3. calculates the ratio R of the characteristic parameter values of adjacent signal long segments, and compares them with the critical threshold R0, if it is larger than the critical threshold, it is regarded as an amplitude surge.
In an embodiment of the identification method, the vibration amplitude characteristic parameter value of step a2 includes a single peak value, an absolute value of the single peak value, and a square value of the peak value.
In an embodiment of the identification method, the step b includes:
b1, counting the number L of the signal long sections of which the vibration characteristic parameter values in the M signal long sections are greater than the benchmarking value A0 after the signal sudden increase;
step b2. calculating the ratio Ra of L/M;
step b3. compares Ra to a benchmarking threshold Ra0 to identify mass fly-off events.
In an embodiment of the identification method, if the mass flight-off event is identified in the step b, the flight-off time, the flight-off mass, and the identification reliability data are output.
A system for identifying a mass flight loss event according to another aspect of the invention comprises: a data processing module comprising a computer-readable storage medium for storing instructions executable by a processor; a processor for executing the instructions to implement the method of any of the above.
In an embodiment of the identification system, the identification system further comprises a measuring module, wherein the measuring module comprises a vibration sensor and a rotating speed sensor, and is used for measuring vibration and rotating speed of the rotor and transmitting measured data to the data processing module.
In an embodiment of the identification system, further comprising a display module for displaying information of a mass flight loss event.
The advantageous effects of the present invention include at least,
1. mass runaway events for aircraft engine rotor components may be identified, and event information including time of occurrence of the runaway event, a runaway mass prediction, a runaway event confidence level may be further determined.
2. The structure of the vibration sensor and the rotation speed sensor of the conventional aircraft engine can be realized, and a complex sensor system is not required to be added, so that the identification system is simple, efficient and low in cost.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a system block diagram of an embodiment of a mass flight loss event identification system according to the present disclosure
Fig. 2 is a flowchart of an embodiment of a method for identifying a mass flight loss event according to the present disclosure.
Fig. 3 is a flowchart of an embodiment of the method for identifying an amplitude spike in the mass flight event according to the present disclosure.
Fig. 4 is a signal segment diagram illustrating an embodiment of the method for identifying a mass flight-off event according to the present invention.
Fig. 5 is a flowchart of an embodiment of determining the amplitude stability of the amplitude sudden increase section according to the method for identifying a mass flight condition.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
Further, it is to be understood that the positional or orientational relationships indicated by the terms "front, rear, upper, lower, left, right", "transverse, vertical, horizontal" and "top, bottom" and the like are generally based on the positional or orientational relationships illustrated in the drawings and are provided for convenience in describing the invention and for simplicity in description, and that these terms are not intended to indicate and imply that the referenced devices or elements must be in a particular orientation or be constructed and operated in a particular orientation without departing from the scope of the invention. As used in this application and the appended claims, the terms "a," "an," "the," and/or "the" are not intended to be inclusive in the singular, but rather are intended to be inclusive in the plural unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that steps and elements are included which are explicitly identified, that the steps and elements do not form an exclusive list, and that a method or apparatus may include other steps or elements.
Also, this application uses specific language to describe embodiments of the application. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
Referring to FIG. 2, in some embodiments, a mass fly-off event of a rotor system of an aircraft engine is exemplified, and a method of identifying a mass fly-off event of an aircraft engine includes
Step a, identifying the amplitude surge of the rotor system according to the fundamental frequency vibration signal of the rotor system;
and b, judging the amplitude stability of the amplitude sudden increase section identified in the step a, and identifying a mass flying-off event.
Specifically, in some embodiments, as shown in fig. 2, the method of obtaining a fundamental frequency (1 octave) vibration signal of a rotor system may include:
step a0., firstly, according to the rotation speed signal, obtaining the magnitude of fundamental frequency (1 frequency multiplication) along with time, and designing a narrow-band-pass tracking filter taking power frequency as central frequency;
step a0. filters the vibration signal of a channel with a tracking filter to obtain a frequency doubled vibration signal.
With reference to fig. 2, in some embodiments, in the step b, a step of determining a sudden increase of the rotation speed may be further provided to eliminate a false determination caused by a sudden increase of the amplitude due to the sudden increase of the rotation speed, for example, a fundamental frequency rotation speed signal may be obtained by using the rotation speed information collected by the rotation speed signal sensor of the rotor system, and compared with the fundamental frequency vibration signal, whether a sudden increase of the rotation speed occurs near the occurrence time of the sudden increase of the amplitude is compared, so as to determine whether the sudden increase of the amplitude is caused by the sudden increase of the rotation speed. Therefore, misjudgment caused by sudden increase of the rotating speed can be effectively avoided, and the accuracy of quality flying-off event identification is further improved.
Referring to fig. 2-4, in some embodiments, the step of identifying an amplitude spike may include:
step a1. dividing the fundamental frequency vibration signal into a plurality of signal segments with zeros; by "zero" is meant the point closest to zero in a small segment of the signal, such as the embodiment shown in fig. 4, which has 23 zeros dividing the signal into 11 small segments;
and a step a2, forming a signal long segment by using N continuous signal small segments, where N is greater than or equal to 2, so as to form a plurality of signal long segments by the plurality of signal small segments, and counting vibration amplitude characteristic parameter values in each signal long segment, specifically, for example, in the embodiment shown in fig. 4, if N is 2, there are 5 signal long segments (represented by L1, L2, L3, L4, and L5) in the figure, where N is an integer greater than or equal to 2, and the embodiment shown in fig. 4 is not limited. The vibration amplitude characteristic parameter values in each signal long segment are counted, and the parameters can be single peak values, absolute values of the single peak values, square values of the single peak values and the like.
Step a3., calculating the ratio R of the characteristic parameter values of the adjacent signal long segments, comparing with the critical threshold R0, if greater than the critical threshold, then regarding as amplitude surge; meanwhile, the time information at the moment can be recorded and output, and the specific output data can be the flying time, the flying quality and the identification reliability data. And calculating the value of R/R0 as one of the estimated basis of the flying-off quality, for example, when an engine test is carried out, the value of R/R0 can be provided for a tester to carry out secondary judgment on whether flying-off occurs or not and the severity of the flying-off event. Although other methods of determining sudden amplitude increases exist, they are not limited to the above description. The amplitude surge identification method has the advantages of simple algorithm, easy identification and judgment and high identification efficiency.
Referring to fig. 2, 5, in some embodiments, the step of identifying the amplitude stability of the amplitude surge segment may include:
step b 1: counting the number N of vibration characteristic parameter values in a plurality of (N0) signal sections after the signal sudden increase, which are greater than the benchmarking value A0;
step b 2: calculating the ratio Ra of N/N0;
step b 3: the Ra is compared with a calibration threshold Ra0 to determine the possibility of occurrence of a mass-off event, and if the occurrence is detected, it is necessary to transmit the result, and the result information includes the reliability of occurrence of the mass-off event estimated based on Ra.
While, for purposes of simplicity of explanation, the methodologies are shown and described as a series of acts, it is to be understood and appreciated that the steps are not limited by the order of acts, as some acts may, in accordance with one or more embodiments, occur in different orders and/or concurrently with other acts from that shown and described herein or not shown and described herein, as would be understood by one skilled in the art.
From the foregoing description, as shown in FIG. 1, a mass flight event identification system includes at least a data processing module including at least a computer readable storage medium for storing instructions executable by a processor; and the processor is used for executing the instructions to realize the identification method of the mass flight-off event. The system can also comprise a measuring module and a display module, wherein the measuring module comprises a vibration sensor, a rotating speed sensor, a data acquisition card and the like which are arranged in an engine system so as to measure the vibration and the rotating speed of an engine rotor, and transmits measured data to the data processing module so as to identify the mass flight-off event of the aircraft engine.
Further, as shown in fig. 1, in some embodiments, the mass-off-flight recognition system may further include a display module for displaying information of an off-flight event, such as data of an off-flight time, an off-flight quality, recognition reliability, and the like, so as to allow an engine research and development tester to further improve the engine, or allow an aircraft operator to feed back engine fault information to help him to deal with a dangerous situation in time.
In summary, the recognition method and the recognition system adopting the above embodiment have the beneficial effects of at least:
1. mass runaway events for aircraft engine rotor components may be identified, and event information including time of occurrence of the runaway event, a runaway mass prediction, a runaway event confidence level may be further determined.
2. The structure of the vibration sensor and the rotation speed sensor of the conventional aircraft engine can be realized, and a complex sensor system is not required to be added, so that the identification system is simple, efficient and low in cost.
Although the present invention has been disclosed in the above-mentioned embodiments, it is not intended to limit the present invention, and those skilled in the art may make variations and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (9)
1. A mass fly-off event identification method for an aircraft engine, comprising:
step a, identifying amplitude surge according to the fundamental frequency vibration signal;
b, judging the amplitude stability of the amplitude sudden increase section identified in the step a, and identifying a mass flying off event; wherein the step of identifying the amplitude spike in the step a comprises:
step a1. dividing the fundamental frequency vibration signal into a plurality of signal segments with a null point, the null point being the point of the segment signal that is closest to zero;
step a2, forming a signal long section by using N continuous signal small sections, wherein N is an integer greater than or equal to 2, so that the plurality of signal small sections form a plurality of signal long sections, and counting vibration amplitude characteristic parameter values in each signal long section;
step a3. calculates the ratio R of the characteristic parameter values of adjacent signal long segments, and compares them with the critical threshold R0, if it is larger than the critical threshold, it is regarded as an amplitude surge.
2. The identification method of claim 1, wherein the method further comprises:
in the step b, the rotating speed sudden increase is identified according to the rotating speed signal so as to eliminate the misjudgment caused by the rotating speed sudden increase.
3. The identification method according to claim 1, wherein the step of obtaining the fundamental frequency vibration signal in step a comprises:
a0., acquiring the change of the fundamental frequency along with time according to the rotating speed signal, and designing a tracking filter taking the power frequency as the center frequency;
and step a01, filtering the vibration signal by adopting the tracking filter to obtain a fundamental frequency vibration signal.
4. The method of identifying as claimed in claim 1, wherein said vibration amplitude characteristic parameter values of said step a2 include a single peak value, an absolute value of a single peak value, a square value of a single peak value.
5. The identification method of claim 1, wherein the step b comprises:
b1, counting the number L of the signal long sections of which the vibration characteristic parameter values in the M signal long sections are greater than the benchmarking value A0 after the signal sudden increase;
step b2. calculating the ratio Ra of L/M;
step b3. compares Ra to a benchmarking threshold Ra0 to identify mass fly-off events.
6. The identification method of claim 1, further comprising:
and b, if the mass flight-out event is identified in the step b, outputting flight-out time, flight-out mass and identification reliability data.
7. A mass fly-off event identification system comprising a data processing module, the data processing module comprising:
a computer-readable storage medium for storing instructions for execution by a processor;
a processor for executing the instructions to implement the method of any one of claims 1 to 6.
8. The mass fly-off event identification system as claimed in claim 7 further comprising:
a measurement module;
the measuring module comprises a vibration sensor and a rotating speed sensor and is used for measuring the vibration and the rotating speed of the rotor and transmitting measured data to the data processing module.
9. The mass fly-off event identification system as claimed in claim 7 further comprising a display module for displaying information of a mass fly-off event.
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| CN102282450A (en) * | 2009-01-13 | 2011-12-14 | 斯奈克玛 | Method and system for monitoring vibratory phenomena occurring in an aircraft's gas turbine engine in operation |
| CN107766611A (en) * | 2017-09-08 | 2018-03-06 | 中国飞行试验研究院 | Power plant accessories system vibration monitoring parameters real-time computing technique in flight test |
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| CN102177313A (en) * | 2008-10-10 | 2011-09-07 | 斯奈克玛 | Method and system for monitoring a turbojet engine |
| CN102282450A (en) * | 2009-01-13 | 2011-12-14 | 斯奈克玛 | Method and system for monitoring vibratory phenomena occurring in an aircraft's gas turbine engine in operation |
| CN101532911A (en) * | 2009-04-24 | 2009-09-16 | 华北电力大学 | Large steam turbine-generator set rotor crack fault real-time diagnosis method |
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