CN111174903A

CN111174903A - Method for diagnosing faults of turbomachinery

Info

Publication number: CN111174903A
Application number: CN201911421176.3A
Authority: CN
Inventors: 王维民; 张旭龙; 宋禹; 余海
Original assignee: Beijing University of Chemical Technology
Current assignee: Beijing University of Chemical Technology
Priority date: 2019-12-31
Filing date: 2019-12-31
Publication date: 2020-05-19
Anticipated expiration: 2039-12-31
Also published as: CN111174903B

Abstract

The invention provides a method for diagnosing a turbomachine fault, and relates to the field of turbomachine vibration monitoring and fault diagnosis. The method comprises the steps of measuring time information of a rotor blade reaching a target position, calculating vibration information of the rotor and the blade, analyzing the vibration information of the rotor and the blade to obtain vibration characteristics of the rotor and the blade, judging fault types of the turbomachine according to the vibration characteristics of the rotor and the blade, and giving an alarm. The diagnosis method for the turbomachinery faults can monitor and early warn typical faults of a turbomachinery rotor-blade system through the arrival time information of the rotor blades, thereby reducing the installation number of sensors, saving the monitoring cost, and being used for vibration monitoring and fault diagnosis during test run of a turbomachinery stand, ground test run and air flight.

Description

Method for diagnosing faults of turbomachinery

Technical Field

The invention relates to the field of vibration monitoring and fault diagnosis of turbomachines, in particular to a diagnosis method for turbomachines faults.

Background

With the implementation of the starting of the 'two-machine special' plan of the aero-engine and the gas turbine, the related industries of turbomachines in China come up with historical development opportunities. Turbine machinery such as an aircraft engine is known as "bright pearl on the industrial crown" due to its complex structure and poor working environment, and the development and production level thereof have become a symbol of national scientific and technological strength. The rotor-blade system of the turbine machinery is very easy to generate forced vibration, mechanical instability and even fatigue fracture under the action of various cyclic alternating loads and pneumatic/structural damping, and meanwhile, the safe, stable and efficient operation of the turbine machinery is seriously influenced by faults such as collision friction between a rotor and a stator, unbalanced vibration of the rotor, bearing abrasion and the like caused by processing and manufacturing errors and operation abrasion. Therefore, it is necessary to monitor and diagnose the vibration of the rotor-blade system of the turbomachine, and the purpose of fault diagnosis and early warning can be achieved by tracking the variation of the vibration characteristic value.

At present, most of the monitoring and diagnosis on the vibration condition of the rotor-blade system are mutually independent and irrelevant, namely, the vibration of the rotor and the blade is respectively monitored through the corresponding monitoring systems, the vibration coupling relation in the rotor-blade system is not considered in the monitoring mode, and meanwhile, the monitoring and diagnosis method has the advantages of large quantity of sensors, complex measuring point arrangement, large system debugging workload, high monitoring and diagnosis cost and low efficiency.

Disclosure of Invention

In view of the above, the present invention provides a method for diagnosing a turbomachine fault, which is based on a vibration coupling relationship in a rotor-blade system and performs monitoring and diagnosis on a typical fault of the rotor-blade system through arrival time information of a rotor blade, thereby reducing the number of sensors to be installed and reducing the cost.

Specifically, the invention provides a method for diagnosing the fault of the turbine machinery, which comprises the following steps:

1) measuring a first arrival time of a key phase reference on the turbomachine to a first target position and a second arrival time of a leading edge of each rotor blade to a second target position and a third arrival time of a trailing edge of each rotor blade to a third target position;

2) calculating a first vibrational displacement, a second vibrational displacement, a first frequency of rotation, a second frequency of rotation, and a twist angle of each rotor blade based on the first time of arrival, the second time of arrival, and the third time of arrival;

3) analyzing the characteristics of the rotor blade vibration based on the first vibration displacement and the second vibration displacement of each rotor blade;

4) and judging the fault type of the turbomachine based on the first rotating frequency, the second rotating frequency and the torsion angle of the rotor blade and the vibration characteristics of the rotor blade.

In a preferred embodiment, the diagnostic method of the invention further comprises the steps of:

5) an alarm is generated based on the type of failure of the turbomachine.

In the invention, the key phase reference on the turbomachine can be a phase reference which exists in real physics, and can also be a virtual reference which is obtained through calculation according to the time of the rotor blade reaching the target position.

Preferably, the rotor blade is a turbomachine fan rotor blade or a compressor rotor blade; the first target position is a measuring point position of a key phase sensor, and is a certain fixed position in the circumferential direction of the rotor when a key phase exists, and is a virtual position when no key phase exists; the second target position is a measuring point position of a sensor arranged on a casing corresponding to the front edge of the rotor blade; and the third target position is a measuring point position of a sensor arranged on the casing corresponding to the trailing edge of the rotor blade.

In a preferred embodiment, step 2) of the process of the invention comprises:

(a) based on the first and second arrival times, calculating a first vibratory displacement of each rotor blade according to the following equation:

(b) based on the first and third arrival times, calculating a second vibratory displacement of each rotor blade according to the following equation:

(c) based on the second arrival time, calculating a first frequency of each rotor blade according to the following formula:

(d) based on the third arrival time, calculating a second rotation frequency of each rotor blade according to the following formula:

(e) based on the first and second vibratory displacements, calculating a twist angle of each rotor blade according to the following equation:

wherein:

for a first vibrational displacement of said each rotor blade,

for a second vibrational displacement of said each rotor blade,

for a first frequency of rotation of said each rotor blade,

for a second frequency of rotation of said each rotor blade,

α_(b,n)for the twist angle of each of said rotor blades,

t_(k,n)the first arrival time at the nth turn is referenced for the key phase,

t_(k,n+1)the first arrival time at the n +1 th turn is referenced for the key phase,

for a second arrival time of said each rotor blade at the nth turn,

for the second arrival time of said each rotor blade at the n +1 th turn,

for a third arrival time of said each rotor blade at the nth turn,

for the third arrival time of said each rotor blade at the n +1 th turn,

is the theoretical arc length between the leading edge of the rotor blade and the key phase reference,

is the theoretical arc length between the rotor blade trailing edge and the key phase reference,

l is the distance of the target position corresponding to the second arrival time and the third arrival time along the axis of the turbine machine,

is the rotorThe included angle between the blade tip of the blade and the axis of the turbine machinery,

the lower corner mark b indicates the rotor blade number, and b is 1,2,3L N_bIn which N is_bThe number of the blades is equal to the total number of the blades,

the lower corner mark k indicates the key phase reference,

the superscript 1 indicates the rotor blade leading edge,

the superscript 2 indicates the rotor blade trailing edge.

In another preferred embodiment, step 3) of the process of the invention comprises:

(f) the synchronous and asynchronous vibrations of each rotor blade were analyzed according to the following method:

based on a first vibrational displacement cluster of said each rotor blade within each damping cycle

Or

Second vibrating displacement cluster

Wherein m is the number of turns of the rotor rotating in each buffering period, m is 20, i is the number of buffering periods, and analyzing

Average value of (2)

And standard deviation of

Or

Average value of (2)

And standard deviation of

At this time, the process of the present invention,

for the first synchronous oscillatory displacement to be the first,

for the second synchronous oscillatory displacement is carried out,

in order to displace in a first asynchronous vibration,

is a second asynchronous vibratory displacement;

(g) the variance and frequency spectrum of the first vibration displacement cluster of the full-leaf and the variance and frequency spectrum of the second vibration displacement cluster of the full-leaf are analyzed according to the following methods:

based on the first vibration displacement cluster of the full blade in each buffering period

Or full-blade second vibration displacement cluster

Adding the vibration displacements of all the blades in the same circle in the full-blade first vibration displacement cluster to obtain a first vibration displacement and a sample

Or adding the vibration displacements of all the blades in the same circle in the second vibration displacement cluster of the whole blade to obtain a second vibration displacement and a sample

Analysis of

Variance of (2)

Or

Variance of (2)

Wherein,

is the variance of the full-leaf first vibrational displacement cluster,

is the variance of the second vibration displacement cluster of the whole blade;

to pair

Or

Carrying out short-time Fourier transform to obtain a first vibration displacement cluster of the whole blade

Spectrum of

Or full-blade second vibration displacement cluster

Spectrum of

(h) Analyzing the pitch diameter of the rotor blade vibration according to the following formula based on the frequency spectrums of at least two full-blade first vibration displacement clusters or the frequency spectrums of full-blade second vibration displacement clusters:

wherein:

ND is the pitch diameter of the rotor blade vibration,

(EO+ND)_Mthe frequencies of main frequency components in the frequency spectrums of at least two full-blade first vibration displacement clusters or the frequencies of main frequency components in the frequency spectrums of at least two full-blade second vibration displacement clusters are obtained, the at least two full-blade first vibration displacement clusters are vibration displacement clusters corresponding to at least two circumferential positions of the front edge of the rotor blade in the rotating direction, and the at least two full-blade second vibration displacement clusters are vibration displacement clusters corresponding to at least two circumferential positions of the rear edge of the rotor blade in the rotating direction;

phi is the phase difference of the main frequency components in the frequency spectrums of the two full-leaf first vibration displacement clusters or the phase difference of the main frequency components in the frequency spectrums of at least two full-leaf second vibration displacement clusters,

theta is the circumferential angular distance between two circumferential positions in the rotating direction corresponding to the two first vibration displacement clusters or the circumferential angular distance between two circumferential positions in the rotating direction corresponding to the two second vibration displacement clusters;

(i) analyzing the frequency multiplication of the rotor blade vibration according to the following method based on the frequency spectrums of at least two full-blade first vibration displacement clusters or the frequency spectrums of full-blade second vibration displacement clusters and the pitch diameter of the rotor blade vibration:

EO＝(EO+ND)_M-ND；

wherein:

EO is the double frequency of the rotor blade vibration, and is the difference frequency part,

ND is the pitch diameter of the rotor blade vibration,

(EO+ND)_Mthe frequencies of the main frequency components in the frequency spectrums of at least two full-blade first vibration displacement clusters or the frequencies of the main frequency components in the frequency spectrums of at least two full-blade second vibration displacement clusters.

In yet another preferred embodiment, step 4) of the process of the invention comprises:

(j) judging whether the rotor blade generates torsional vibration or not based on the torsional angle of each rotor blade, and if the first vibration displacement and the second vibration displacement of the rotor blade measured at the same moment are not equal, namely alpha_(b,n)If not equal to 0, judging that the rotor blade generates torsional vibration;

(k) judging whether the rotor blades generate synchronous vibration or not based on the first synchronous vibration displacement and the second synchronous vibration displacement of each rotor blade, if the rotor blades rotate to a certain rotating speed, the first synchronous vibration displacement and the second synchronous vibration displacement are suddenly increased and are reduced to the original level after the rotating speed, judging that the rotor blades generate synchronous vibration, and if the corresponding rotating speed is reduced when the blades synchronously vibrate, judging that the blades generate cracks;

(l) Judging whether the rotor blade generates asynchronous vibration or not based on the first asynchronous vibration displacement and the second asynchronous vibration displacement of each rotor blade, and judging that the rotor blade generates asynchronous vibration if the first asynchronous vibration displacement and the second asynchronous vibration displacement are suddenly increased when the rotor blade rotates to a certain rotating speed or the load is changed;

(m) judging whether the rotor blade stalls or surges based on the first asynchronous vibration displacement, the second asynchronous vibration displacement, the frequency spectrum of the full-blade first vibration displacement cluster and the frequency spectrum of the full-blade second vibration displacement cluster of each rotor blade, if the rotor blade rotates to a certain rotating speed or the aerodynamic load changes, the rotating speed of the blade tip irregularly fluctuates, the first asynchronous vibration displacement and the second asynchronous vibration displacement increase, and non-integer frequency multiplication components appear in the frequency spectrum of the full-blade first vibration displacement cluster and the frequency spectrum of the full-blade second vibration displacement cluster, the turbomachinery is judged to stall,

(n) after the stall is generated, if the first asynchronous vibration displacement and the second asynchronous vibration displacement are continuously increased, the turbine mechanical noise fluctuation is severe, the non-integer frequency multiplication component amplitude in the frequency spectrum of the full-blade first vibration displacement cluster and the frequency spectrum of the full-blade second vibration displacement cluster is increased,becomes the dominant frequency component, i.e. (EO + ND)_MJudging that the turbo machinery has surging if the number is non-integer;

(o) determining whether the rotor blade has flutter based on the first vibration displacement, the second vibration displacement, the torsion angle of each rotor blade and the pitch diameter of the rotor blade vibration, wherein if the rotor blade is operated to a certain rotation speed or the aerodynamic load changes, the first vibration displacement and the second vibration displacement are increased, and the rotor blade vibration mode is pitch diameter type bending-torsion coupled vibration, namely α_(b,n)If not equal to 0 and ND not equal to 0, judging that the turbo machinery generates flutter;

(p) determining whether a rotor-seal rub-on or a rotor thermal bending has occurred based on the first vibration displacement, the second vibration displacement, the first frequency of rotation, and the second frequency of rotation of each rotor blade, and if the first vibration displacement, the second vibration displacement, the first frequency of rotation, and the second frequency of rotation of one or a part of the rotor blades among all the rotor blades are different from the remaining rotor blades when the rotor blades are operated in the low-speed non-resonance region and the difference is greater and greater with the increase of the continuous operation time, determining that a rotor-seal rub-on failure has occurred in the turbomachine,

the rotor is thermally bent due to long-time rotor-seal rubbing, so that the difference between the first vibration displacement, the second vibration displacement, the first rotating frequency and the second rotating frequency of each rotor blade under the same working condition is larger and larger;

(q) judging whether blade-casing rub impact occurs or not based on the first and second rotating frequencies of each rotor blade, and if the first rotating frequency or the second rotating frequency of a certain rotor blade fluctuates in the operation process of the rotor blade, judging that single-point rub impact occurs between the rotor blade of the turbomachine and the casing, wherein the rub impact position is a position corresponding to the rotor blade of which the first rotating frequency or the second rotating frequency fluctuates;

(r) judging whether bearing damage occurs or not based on the variance of each first full-blade vibration displacement cluster and the variance of each second full-blade vibration displacement cluster, if the rotor blade runs, the variance of the first full-blade vibration displacement cluster and the variance of the second full-blade vibration displacement cluster increase, judging that the bearing close to the rotor blade is slightly damaged, and along with the increase of the running time, if the variance of the first full-blade vibration displacement cluster and the variance of the second full-blade vibration displacement cluster gradually decrease and tend to be stable, judging that the bearing damage is aggravated until the variance of the first full-blade vibration displacement cluster and the variance of the second full-blade vibration displacement cluster sharply decrease again, and judging that the turbomachine bearing fails;

in another aspect, the present invention provides a diagnostic apparatus for a failure of a turbomachine, the diagnostic apparatus comprising:

a measurement module: measuring a first arrival time of a key phase reference on the turbomachine to a first target position, a second arrival time of a leading edge of each rotor blade to a second target position, and a third arrival time of a trailing edge of each rotor blade to a third target position;

a calculation module: calculating a first vibrational displacement, a second vibrational displacement, a first frequency of rotation, a second frequency of rotation, and a twist angle of a rotor blade of the turbomachine based on the first time of arrival, the second time of arrival, and the third time of arrival;

an analysis module: the system is used for analyzing the characteristics of the vibration of the rotor blades, including synchronous vibration, asynchronous vibration, variance, frequency spectrum, pitch diameter and frequency multiplication, based on the first vibration displacement and the second vibration displacement of each rotor blade;

a judging module: the method is used for judging the fault type of the turbomachine based on the first rotating frequency, the second rotating frequency and the torsion angle of the rotor blade and the vibration characteristics of the rotor blade; and

an alarm module: for alarming based on the type of failure of the turbomachine.

In still another aspect, the present invention provides an electronic device, which includes a processor, a memory and a bus, wherein the processor and the memory communicate with each other via the bus when the electronic device is running, the memory stores machine-readable instructions executable by the processor, and the machine-readable instructions, when executed by the processor, perform the method for diagnosing the turbomachine fault according to the present invention as described above.

In yet another aspect, the present invention provides a computer-readable storage medium having stored thereon a computer program which, when executed by a processor, performs the steps of the method for diagnosing a turbomachine fault as described above.

The diagnosis method of the invention calculates the first vibration displacement, the second vibration displacement and the first rotating frequency of each rotor blade based on the first arrival time, the second arrival time and the third arrival time by measuring the first arrival time of key phase reference on the turbomachine to reach the first target position, the second arrival time of each rotor blade leading edge to reach the second target position and the third arrival time of each rotor blade trailing edge to reach the third target position, and the second frequency conversion and torsion angle are used for analyzing the vibration characteristics of the rotor blades based on the first vibration displacement and the second vibration displacement of each rotor blade, judging the fault type of the turbomachine based on the first frequency conversion, the second frequency conversion and the torsion angle of the rotor blades and the vibration characteristics of the rotor blades, and giving an alarm based on the fault type of the turbomachine. Compared with the diagnosis method of the turbine mechanical fault in the prior art, the method can monitor and early warn the typical fault of the rotor-blade system through the arrival time information of the rotor blade, greatly reduces the workload of installation and debugging and saves the monitoring cost. The invention can be used for vibration monitoring and diagnosis during test run of the turbine mechanical rack and ground test run, and can also be used for monitoring and diagnosis of turbine units such as a gas turbine and the like.

Drawings

In order to more clearly illustrate the invention, the following figures will be provided. It is appreciated that the following drawings depict only certain embodiments of the application and are therefore not to be considered limiting of its scope, for those skilled in the art will be able to derive additional related drawings therefrom without the benefit of the inventive faculty.

FIG. 1 is a system architecture diagram of an application scenario of aircraft engine fault diagnosis;

FIG. 2 is a flow chart of an embodiment of a diagnostic method of the present invention;

FIG. 3 is an exemplary illustration of a first vibrational displacement of a rotor blade;

FIG. 4 is an exemplary illustration of a first synchronous vibratory displacement and a first asynchronous vibratory displacement of a rotor blade;

FIG. 5 is an exemplary graph of a full-leaf first vibration displacement cluster and its frequency spectrum;

FIG. 6 is a schematic structural diagram of an embodiment of the fault diagnosis apparatus of the present invention;

FIG. 7 is a schematic structural view of the measurement module shown in FIG. 6;

FIG. 8 is a schematic diagram of the computing module shown in FIG. 6;

FIG. 9 is a schematic diagram of the analysis module shown in FIG. 6;

FIG. 10 is a schematic structural diagram of the determining module shown in FIG. 6;

FIG. 11 is a schematic diagram of the alarm module shown in FIG. 6;

fig. 12 is a schematic structural diagram of an embodiment of an electronic device according to the invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention will be described in detail and completely with reference to the accompanying drawings. The components generally described and illustrated in the figures may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the application. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present application without making any creative effort, shall fall within the protection scope of the present invention.

In the present application, the term "turbomachine" includes, but is not limited to, an aircraft engine, a gas turbine, a turbocharger, various compressors and turbines, and the like, preferably referring to an aircraft engine and/or a gas turbine.

First, an application scenario to which the present application is applicable will be described. The invention can be applied to vibration monitoring and diagnosis during test run of the turbine mechanical rack and ground test run, and can also be applied to monitoring and diagnosis of turbine units such as a gas turbine and the like.

Referring to fig. 1, fig. 1 is a system architecture diagram in an application scenario of aircraft engine fault diagnosis. As shown in FIG. 1, the system comprises a turbomachine fault diagnosis device, an application server and a plurality of aircraft engines, wherein the fault diagnosis device is connected with the application server, data of a first arrival time, a second arrival time and a third arrival time of each aircraft engine can be called from the application server, and the application server can collect the data of the first arrival time, the second arrival time and the third arrival time of each aircraft engine. In the above example, the fault diagnosis device is connected to the application server to retrieve data from the application server, but the fault diagnosis device is not limited to this, and in other examples, the fault diagnosis device may be connected to the application server, and may also be directly connected to each turbomachine, for example, an aircraft engine, or may be connected to a database or the like to retrieve data of the turbomachine, for example, the aircraft engine.

Research shows that most of the monitoring and diagnosis of the vibration condition of the rotor-blade system are independent and irrelevant, namely the vibration of the rotor and the blade is respectively monitored through the corresponding monitoring system, the vibration coupling relation in the rotor-blade system is not considered in the monitoring mode, and meanwhile, the number of the required sensors is large, the measuring point arrangement is complicated, the monitoring and diagnosis cost is high, and the efficiency is low.

Based on the method, the typical faults of the rotor-blade system are monitored and diagnosed through the arrival time information of the rotor blades, so that the number of sensors is reduced, and the cost is reduced.

FIG. 2 is a flow chart of an embodiment of a turbomachine fault diagnostic method of the present invention, as shown in FIG. 2, the diagnostic method comprising:

step 201: a first arrival time of a key phase reference on the aircraft engine to reach the first target position, a second arrival time of each rotor blade leading edge to reach the second target position and a third arrival time of each rotor blade trailing edge to reach the third target position are measured.

In this step, the key phase reference on the aero-engine may be a phase reference that exists in a real physical environment, or may be a virtual reference that is calculated according to a time when a rotor blade reaches a target position, where the rotor blade is a fan rotor blade or a compressor rotor blade of the aero-engine, the first target position is a key phase sensor measuring point position, the first target position is a certain fixed position in the circumferential direction of the rotor when the key phase exists, the second target position is a virtual position when the key phase does not exist, the second target position is a measuring point position of a sensor mounted on a casing corresponding to a leading edge of the rotor blade, and the third target position is a measuring point position of a sensor mounted on a casing corresponding to a trailing edge of the rotor blade.

Step 202: calculating a first vibrational displacement, a second vibrational displacement, a first rotational frequency, a second rotational frequency, and a twist angle of each rotor blade based on the first arrival time, the second arrival time, and the third arrival time.

In this step, a first vibration displacement of each rotor blade is calculated based on the first arrival time and the second arrival time, a second vibration displacement of each rotor blade is calculated based on the first arrival time and the third arrival time, a first frequency of each rotor blade is calculated based on the second arrival time, and a second frequency of each rotor blade is calculated based on the third arrival time. Specifically, the tip linear velocity of the rotor blade may be calculated according to the first arrival time and the tip diameter of the rotor blade, then the arc length between the measured tip leading edge and the key phase reference may be calculated according to the time difference between the second arrival time and the first arrival time and the tip linear velocity, and the theoretical arc length is subtracted from the measured arc length to obtain the vibration displacement of the tip leading edge, which is recorded as the first vibration displacement. The reciprocal of the time difference between the two second arrival times of the two adjacent circles corresponding to the front edge of each rotor blade is the first frequency conversion of the corresponding rotor blade, and the reciprocal of the time difference between the two third arrival times of the two adjacent circles corresponding to the rear edge of each rotor blade is the second frequency conversion of the corresponding rotor blade.

After the first vibration displacement and the second vibration displacement of each rotor blade are obtained through calculation, further calculation may be performed, and the torsion angle of each rotor blade may be calculated using the first vibration displacement and the second vibration displacement of each rotor blade. Specifically, the included angle between the blade tip of the rotor blade and the axis of the engine is calculated according to the relative position relationship between the second optical sensor and the third optical sensor which are arranged on the casing at the positions corresponding to the front edge and the rear edge of the blade tip, and the included angle between the blade tip of the rotor blade and the axis of the engine when the rotor blade is not deformed is subtracted, so that the torsion angle of the rotor blade can be obtained.

Step 203: and analyzing the characteristics of the vibration of the rotor blades based on the first vibration displacement and the second vibration displacement of each rotor blade.

In the step, after the first vibration displacement and the second vibration displacement of each rotor blade are obtained through calculation, the first vibration displacement and the second vibration displacement are analyzed, and the characteristics of the vibration of the rotor blades, including synchronous vibration, asynchronous vibration, frequency spectrum, pitch diameter and frequency multiplication, are analyzed.

Specifically, the average value and the standard deviation of the first vibration displacement cluster or the second vibration displacement cluster of each rotor blade in each buffering period are analyzed, the obtained average value is synchronous vibration displacement, the standard deviation is asynchronous vibration displacement, the rotor blade rotates for 20 circles to form a buffering period, and the synchronous vibration displacement and the asynchronous vibration displacement obtained by analyzing the first vibration displacement cluster and the second vibration displacement cluster are consistent under the condition that the blade is not twisted, so that the first vibration displacement cluster can be selected for analysis, and the second vibration displacement cluster can also be selected for analysis. Then analyzing variance and frequency spectrum based on a full-blade first vibration displacement cluster or a full-blade second vibration displacement cluster in each buffering period, wherein the full-blade first vibration displacement cluster in each buffering period is a displacement cluster obtained by arranging the first vibration displacement of each rotor blade in 20 circles of rotor rotation according to the time sequence, the full-blade second vibration displacement cluster in each buffering period is a displacement cluster obtained by arranging the second vibration displacement of each rotor blade in 20 circles of rotor rotation according to the time sequence, the vibration displacements of all blades in the same circle in the full-blade first vibration displacement cluster are added to obtain a first vibration displacement and a sample, the variance of the first vibration displacement cluster of the full-blade is obtained by analyzing the variance, or the vibration displacements of all blades in the same circle in the full-blade second vibration displacement cluster are added to obtain a second vibration displacement and a sample, and analyzing the variance to obtain the variance of the full-blade second vibration displacement cluster, and performing short-time Fourier transform on the full-blade first vibration displacement cluster or the full-blade second vibration displacement cluster to obtain the frequency spectrum of the full-blade first vibration displacement cluster or the frequency spectrum of the full-blade second vibration displacement cluster. And then analyzing the pitch diameter of the rotor blade vibration by combining the circumferential angular intervals of two circumferential positions in the rotating direction corresponding to the two first vibration displacement clusters or the two second vibration displacement clusters based on the phase difference of main frequency components in the frequency spectrums of at least two first vibration displacement clusters of the full blades or the frequency spectrums of second vibration displacement clusters of the full blades. And finally, analyzing the frequency multiplication of the rotor blade vibration based on the frequency spectrums of the at least two full-blade first vibration displacement clusters or the main frequency components in the frequency spectrums of the full-blade second vibration displacement clusters and the pitch diameter of the rotor blade vibration, wherein the frequency multiplication obtained by analysis is a difference frequency part due to the undersampling of the measuring method.

For example, fig. 3 is an exemplary graph of the first vibration displacement of a certain rotor blade, the average value and the standard deviation of the first vibration displacement cluster of the rotor blade in each buffering period in fig. 3 are analyzed, the obtained average value is the first synchronous vibration displacement, the standard deviation is the first asynchronous vibration displacement, fig. 4 is an exemplary graph of the first synchronous vibration displacement and the first asynchronous vibration displacement of the rotor blade, 20 revolutions are taken from the first vibration displacement of each rotor blade to form a full-blade first vibration displacement cluster from the revolution of 9375 in fig. 3, fig. 5 is an exemplary graph of the full-blade first vibration displacement cluster and the frequency spectrum thereof, as shown in (1) in fig. 5, the full-blade first vibration displacement cluster is subjected to short-time fourier transform, and the frequency spectrum of the full-blade first vibration displacement cluster shown in (2) in fig. 5 is obtained.

Step 204: and judging the fault types of the aircraft engine and the gas turbine based on the first rotating frequency, the second rotating frequency and the torsion angle of the rotor blade and the vibration characteristics of the rotor blade.

In this step, the fault type of the turbomachine, including torsional vibration, synchronous vibration, asynchronous vibration, stall, surge, flutter, rotor-seal rub-on, rotor thermal bending, blade-casing rub-on, and bearing damage, is determined according to the first frequency of rotation, the second frequency of rotation, the torsional angle of the rotor blade, and the characteristics of the rotor blade vibration.

Specifically, when the torsion angle of the rotor blade is not 0, it is determined that the rotor blade has torsional vibration; when the rotor blade rotates to a certain rotating speed, the first synchronous vibration displacement and the second synchronous vibration displacement are suddenly increased, the rotor blade is judged to generate synchronous vibration when the rotor blade passes through a synchronous resonance point, and if the rotating speed corresponding to the synchronous resonance of the blade is reduced relative to the rotating speed corresponding to the same synchronous resonance point in the prior art, the inherent frequency of the blade is reduced, and the crack is judged to occur; when the rotor blade rotates to a certain rotating speed or the load changes, the first asynchronous vibration displacement and the second asynchronous vibration displacement are suddenly increased, and then the rotor blade is judged to generate asynchronous vibration; when the rotor blade rotates to a certain rotating speed or the pneumatic load changes, the rotating speed of the blade tip irregularly fluctuates, the first asynchronous vibration displacement and the second asynchronous vibration displacement are increased, the frequency spectrum of the first vibration displacement cluster of the full blade and the frequency spectrum of the second vibration displacement cluster of the full blade have non-integer frequency multiplication components, the engine is judged to stall, the stall is a premonitory article of surging, and after the stall is generated, if the first asynchronous vibration displacement and the second asynchronous vibration displacement are continuously increased, the noise of the engine severely fluctuates, and the non-integer frequency multiplication component amplitude values in the frequency spectrum of the first vibration displacement cluster of the full blade and the frequency spectrum of the second vibration displacement cluster of the full blade are increased to become a main frequency component, the engine is judged to surge; when the rotor blade rotates to a certain rotating speed or the pneumatic load changes, the first vibration displacement and the second vibration displacement are increased, the torsion angle and the vibration pitch diameter of the rotor blade are not 0, and the engine is judged to vibrate; if the first vibration displacement, the second vibration displacement, the first frequency conversion and the second frequency conversion of one or a part of the rotor blades of all the rotor blades are different from the rest of the rotor blades when the rotor blades operate in the low-speed non-resonance region, and the difference is larger and larger along with the increase of the continuous operation time, the rotor-seal rubbing fault of the engine is judged to occur, the rotor is thermally bent due to the long-time rotor-seal rubbing, and the difference between the first vibration displacement, the second vibration displacement, the first frequency conversion and the second frequency conversion of each rotor blade is larger and larger under the same working condition; if the first rotating frequency or the second rotating frequency of a certain rotor blade fluctuates in the running process of the rotor blade, judging that the single-point rubbing of the rotor blade of the engine and the casing occurs, wherein the rubbing position is the position corresponding to the rotor blade with the first rotating frequency or the second rotating frequency fluctuating; and judging whether the bearing damage occurs or not based on the variance of each first full-blade vibration displacement cluster and the variance of each second full-blade vibration displacement cluster, if the rotor blade runs, the variance of the first full-blade vibration displacement cluster and the variance of the second full-blade vibration displacement cluster increase, judging that the bearing close to the rotor blade slightly damages, and along with the increase of the running time, if the variance of the first full-blade vibration displacement cluster and the variance of the second full-blade vibration displacement cluster gradually decrease and tend to be stable, judging that the bearing damage is aggravated until the variance of the first full-blade vibration displacement cluster and the variance of the second full-blade vibration displacement cluster sharply decrease again, and judging that the turbomachine bearing fails.

For example, if the first asynchronous vibration displacement of the rotor blade in fig. 4 is suddenly increased, it is determined that the engine has asynchronous vibration, and the frequency spectrum of (2) the full-blade first vibration displacement cluster in fig. 5 has a non-integer main frequency component of 2.55, and it is determined that the engine has surge by combining fig. 4 and 5.

Therefore, the fault types of the aircraft engine and the gas turbine are judged according to the vibration characteristics of the rotor blades, the monitoring and diagnosis of the typical faults of the rotor-blade system of the aircraft engine and the gas turbine are realized by only using three optical sensors and combining the vibration coupling relation in the rotor-blade system, the utilization rate of the sensors is improved, the installation and debugging workload is greatly reduced, and the monitoring cost is saved.

Step 205: and alarming based on the fault types of the aero-engine and the gas turbine.

In the step, after the fault types of the aero-engine and the gas turbine are obtained, the alarm module gives an alarm based on the fault types of the aero-engine and the gas turbine. The alarm can prevent further deterioration of the fault, prevent accidents, and simultaneously prompt the type of the fault and the position of the fault, so that targeted maintenance can be performed, the maintenance of the whole machine is avoided, and manpower and material resource investment is saved.

The diagnostic method of the present invention measures the time of arrival of the leading edge of each rotor blade at the first target position and the time of arrival of the trailing edge of each rotor blade at the second target position and the time of arrival of the trailing edge of each rotor blade at the third target position by measuring the first time of arrival of the key phase reference on the turbomachine such as an aircraft engine, calculating a first vibration displacement, a second vibration displacement, a first rotating frequency, a second rotating frequency and a torsion angle of each rotor blade based on the first arrival time, the second arrival time and the third arrival time, analyzing the characteristics of the vibration of the rotor blades based on the first vibration displacement and the second vibration displacement of each rotor blade, judging the fault type of a turbomachine such as an aircraft engine based on the first rotating frequency, the second rotating frequency and the torsion angle of the rotor blades and the characteristics of the vibration of the rotor blades, and alarming based on the fault type of the turbomachine such as the aircraft engine.

Compared with the diagnosis method of the turbine machinery fault in the prior art, the invention only utilizes three sensors to measure the arrival time information of the rotor blade, and combines the vibration coupling relation in the rotor-blade system to realize the monitoring and early warning of the typical fault of the rotor-blade system, greatly reduces the installation and debugging workload and saves the monitoring cost, can be widely used for the vibration monitoring and diagnosis during the test run of the turbine machinery rack and the ground test run, and can also be used for the monitoring and diagnosis of turbine units such as a gas turbine and the like.

Fig. 6 is a schematic structural diagram of an embodiment of the fault diagnosis device of the present invention, fig. 7 is a schematic structural diagram of a measurement module shown in fig. 6, fig. 8 is a schematic structural diagram of a calculation module shown in fig. 6, fig. 9 is a schematic structural diagram of an analysis module shown in fig. 6, fig. 10 is a schematic structural diagram of a judgment module shown in fig. 6, and fig. 11 is a schematic structural diagram of an alarm module shown in fig. 6. As shown in fig. 6, the failure diagnosis apparatus 600 includes:

the measurement module 610: the method is used for measuring a first arrival time of a key phase reference on a turbomachine such as an aircraft engine to reach a first target position, a second arrival time of a leading edge of each rotor blade to reach a second target position and a third arrival time of a trailing edge of each rotor blade to reach a third target position.

The calculation module 620: the method includes calculating a first vibrational displacement, a second vibrational displacement, a first frequency of rotation, a second frequency of rotation, and a twist angle of a rotor blade of the turbomachine, such as an aircraft engine, a gas turbine, based on the first time of arrival, the second time of arrival, and the third time of arrival.

The analysis module 630: the method is used for analyzing the characteristics of the vibration of the rotor blades, including synchronous vibration, asynchronous vibration, variance, frequency spectrum, pitch diameter and frequency multiplication, based on the first vibration displacement and the second vibration displacement of each rotor blade.

The judging module 640: the method is used for judging the fault type of the turbomachinery such as an aircraft engine and a gas turbine based on the first rotating frequency, the second rotating frequency and the torsion angle of the rotor blade and the characteristics of the vibration of the rotor blade.

The alarm module 650: for alarming based on the type of failure of said turbomachinery, such as aircraft engines, gas turbines.

Optionally, as shown in fig. 7, the measurement module 610 includes:

a first optical sensor 611 mounted at one side of the rotor blade drive shaft for measuring a first arrival time of the key phase reference at the first target position and providing a reference for the vibration of the rotor blade;

a second optical sensor 612, mounted on the casing corresponding to the position of the leading edge of the rotor blade, is used for measuring a second arrival time of each leading edge of the rotor blade at a second target position.

And a third optical sensor 613, which is installed on the casing corresponding to the position of the trailing edge of the rotor blade, for measuring a third arrival time of the trailing edge of each rotor blade at a third target position.

A laser 614 for providing a light source to the first, second, third optical sensors.

And an optical-to-electrical converter 615 for converting optical signals reflected by the object to be measured received by the first optical sensor, the second optical sensor and the third optical sensor into electrical signals.

And a data collector 616 for collecting the electrical signal output by the photoelectric converter and converting the electrical signal into an arrival time sequence according to the level of the electrical signal.

Optionally, as shown in fig. 8, the calculating module 620 includes:

a first calculation module 621 for calculating a first vibratory displacement of each rotor blade based on the first arrival time and the second arrival time;

a second calculation module 622 for calculating a second vibratory displacement of each rotor blade based on the first arrival time and the third arrival time;

a third calculation module 623 for calculating a first rotation frequency for each rotor blade based on the second arrival time;

a fourth calculation module 624 for calculating a second rotation frequency for each rotor blade based on the third arrival time;

a fifth calculation module 625 for calculating a twist angle of each rotor blade based on the first vibrational displacement and the second vibrational displacement.

Optionally, as shown in fig. 9, the analysis module 630 includes:

a first analyzing module 631 for analyzing the synchronous vibration and the asynchronous vibration of each rotor blade based on the first vibration displacement and the second vibration displacement of each rotor blade;

a second analysis module 632 for analyzing a variance and a frequency spectrum of a full-blade first vibration displacement cluster and a variance and a frequency spectrum of a full-blade second vibration displacement cluster based on the first vibration displacement or the second vibration displacement of each rotor blade;

a third analysis module 633 for analyzing pitch diameters of rotor blade vibrations based on frequency spectra of at least two of said full-blade first vibrational displacement clusters or frequency spectra of full-blade second vibrational displacement clusters;

a fourth analysis module 634 for analyzing a multiple frequency of the rotor blade vibration based on at least two of the frequency spectra of the full-blade first vibration displacement cluster or the frequency spectra of the full-blade second vibration displacement cluster, and the pitch diameter of the rotor blade vibration.

Optionally, as shown in fig. 10, the determining module 640 includes:

a first determining module 641 for determining whether a torsional vibration has occurred in the rotor blade based on the torsional angle of each rotor blade;

a second determining module 642, configured to determine whether a synchronous vibration or a blade crack occurs in the rotor blade based on the first synchronous vibration displacement and the second synchronous vibration displacement of each rotor blade;

a third determining module 643, configured to determine whether the rotor blade is asynchronously vibrated based on the first asynchronous vibration displacement and the second asynchronous vibration displacement of each rotor blade;

a fourth determining module 644, configured to determine whether a stall or surge occurs in the rotor blade based on the first asynchronous vibration displacement, the second asynchronous vibration displacement, the frequency spectrum of the full-blade first vibration displacement cluster, and the frequency spectrum of the full-blade second vibration displacement cluster of each rotor blade;

a fifth determining module 645, configured to determine whether the rotor blade flutters based on the first vibration displacement, the second vibration displacement, the torsion angle of each rotor blade, and the pitch diameter of the rotor blade vibration;

a sixth determining module 646, configured to determine whether rotor-seal rubbing or rotor thermal bending occurs based on the first vibration displacement, the second vibration displacement, the first rotation frequency, and the second rotation frequency of each rotor blade;

a seventh determining module 647, configured to determine whether a blade-casing rub impact occurs based on the first and second rotation frequencies of each rotor blade;

an eighth determining module 648, configured to determine whether bearing damage occurs based on the variance of each full-blade first vibrational displacement cluster and the variance of each full-blade second vibrational displacement cluster.

Optionally, as shown in fig. 11, the alarm module 650 includes:

a first alarm indicator 651 for indicating whether the rotor blade is torsionally vibrated, the first alarm indicator being turned on when the rotor blade is torsionally vibrated;

a second alarm indicator 652 for indicating whether the rotor blade has a synchronous vibration or a blade crack, and when the rotor blade has a synchronous vibration or a blade crack, the second alarm indicator is turned on;

a third alarm light 653, which is used to indicate whether the rotor blade has asynchronous vibration, and when the rotor blade has asynchronous vibration, the third alarm light is on;

a fourth warning indicator 654 for indicating whether the rotor blade is stalled or surging, the fourth warning indicator being lit when the rotor blade is stalled or surging;

a fifth warning indicator 655 for indicating whether the rotor blade flutters, the fifth warning indicator being lit when the rotor blade flutters;

a sixth alarm indicating lamp 656, which is used for indicating whether rotor-seal rubbing or rotor thermal bending occurs, and is turned on when rotor-seal rubbing or rotor thermal bending occurs;

a seventh alarm indicating lamp 657 for indicating whether or not the blade-casing rub-impact occurs, the seventh alarm indicating lamp being on when the blade-casing rub-impact occurs;

and an eighth alarm light 658 for indicating whether bearing damage has occurred, and when bearing damage occurs, the eighth alarm light is turned on.

The invention relates to a turbomachine fault diagnosis device, which is characterized in that a first arrival time of a key phase reference on a turbomachine to reach a first target position, a second arrival time of a front edge of each rotor blade to reach a second target position and a third arrival time of a rear edge of each rotor blade to reach a third target position are measured; calculating a first vibration displacement, a second vibration displacement, a first frequency conversion, a second frequency conversion and a torsion angle of each rotor blade based on the first arrival time, the second arrival time and the third arrival time, analyzing the characteristics of the vibration of the rotor blades based on the first vibration displacement and the second vibration displacement of each rotor blade, judging the fault type of the turbomachine based on the first frequency conversion, the second frequency conversion and the torsion angle of the rotor blades and the characteristics of the vibration of the rotor blades, and giving an alarm based on the fault type of the turbomachine.

Compared with the diagnosis method of the turbine machinery fault in the prior art, the invention only utilizes three optical sensors to measure the arrival time information of the rotor blade, and combines the vibration coupling relation in the rotor-blade system, thereby realizing the monitoring and early warning of the typical fault of the rotor-blade system, improving the utilization rate of the sensors, greatly reducing the installation and debugging workload and saving the monitoring cost, and being widely applied to the vibration monitoring and diagnosis during the test run of the turbine machinery rack and the ground test run, and also being applied to the monitoring and diagnosis of turbine units such as a gas turbine and the like.

Fig. 12 is a schematic structural diagram of an embodiment of an electronic device according to the invention. As shown in fig. 12, the electronic device 1200 includes a processor 1210, a memory 1220, and a bus 1230.

The memory 1220 stores machine-readable instructions (for example, execution instructions corresponding to the calculation module 620, the analysis module 630, the determination module 640, and the alarm module 650 in fig. 6) executable by the processor 1210, when the electronic device 1200 runs, the processor 1210 communicates with the memory 1220 through the bus 1230, and when the machine-readable instructions are executed by the processor 1210, all steps of the diagnosis method for turbine mechanical failure in the embodiment of the method shown in fig. 2 may be executed.

The present invention further provides a computer-readable storage medium, where a computer program is stored on the computer-readable storage medium, and when the computer program is executed by a processor, all steps of the method for diagnosing a turbomachine fault in the embodiment of the method shown in fig. 2 may be executed.

It can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working processes of the above-described apparatuses and modules may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.

In the several embodiments provided in the present application, it should be understood that the disclosed apparatus, module, and method may be implemented in other ways. The above-described embodiments of the apparatus are merely illustrative, and for example, the division of the modules is only one logical division, and there may be other divisions when actually implemented, and for example, a plurality of modules may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, functional modules in the embodiments of the present application may be integrated into one processing module, or each of the modules may exist alone physically, or two or more modules are integrated into one module.

The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a non-volatile computer-readable storage medium executable by a processor. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: various media capable of storing program codes, such as a usb disk, a removable hard disk, a Read-only Memory (ROM), a Random Access Memory (RAM), a magnetic disk, or an optical disk.

Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present application, and are used for illustrating the technical solutions of the present application, but not limiting the same, and the protection scope of the present invention is not limited thereto, although the present application is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: any person skilled in the art can modify or easily conceive the technical solutions described in the foregoing embodiments or equivalent substitutes for some technical features within the technical scope disclosed in the present application; such modifications, changes or substitutions do not depart from the spirit and scope of the present disclosure, and should be construed as being included therein. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A method of diagnosing a turbomachine fault, said method comprising the steps of:

2) calculating a first vibrational displacement, a second vibrational displacement, a first rotational frequency, a second rotational frequency, and a twist angle of each rotor blade based on the first, second, and third arrival times;

3) analyzing a characteristic of rotor blade vibration based on the first and second vibratory displacements of each rotor blade; and

4) and judging the fault type of the turbomachine based on the first rotating frequency, the second rotating frequency and the torsion angle of each rotor blade and the characteristics of the vibration of the rotor blades.

2. The method of claim 1, wherein the method further comprises the steps of:

5) an alarm is generated based on the type of failure of the turbomachine.

3. The method of claim 1 or 2, wherein:

the key phase reference on the turbomachinery is a phase reference which exists in a real physical mode or a virtual reference which is obtained through calculation according to the time of the rotor blade reaching the target position;

the rotor blade is a turbomachine fan rotor blade or a gas compressor rotor blade;

the first target position is a measuring point position of a key phase sensor, and is a certain fixed position in the circumferential direction of the rotor when a key phase exists, and is a virtual position when no key phase exists;

the second target position is a measuring point position of a sensor arranged on a casing corresponding to the front edge of the rotor blade; and

and the third target position is a measuring point position of a sensor arranged on the casing corresponding to the trailing edge of the rotor blade.

4. The method as set forth in claim 3, wherein the step 2) includes:

wherein:

for a first vibrational displacement of said each rotor blade,

for a second vibrational displacement of said each rotor blade,

for a first frequency of rotation of said each rotor blade,

for a second frequency of rotation of said each rotor blade,

α_(b,n)for the twist angle of each of said rotor blades,

t_(k,n)the first arrival time at the nth turn is referenced for the key phase,

for a second arrival time of said each rotor blade at the nth turn,

for the second arrival time at the n +1 th turn of said each rotor blade,

for a third arrival time of said each rotor blade at the nth turn,

for the third arrival time of said each rotor blade at the n +1 th turn,

l is the distance of the second target position and the third target position along the axis of the turbomachine,

is the included angle between the blade tip of the rotor blade and the axis of the turbine machinery,

the lower corner b indicates the number of the rotor blade, and b is 1,2,3 … N_bIn which N is_bThe number of the blades is equal to the total number of the blades,

the lower corner mark k indicates the key phase reference,

the superscript 1 denotes the rotor blade leading edge, an

The superscript 2 indicates the rotor blade trailing edge.

5. The method according to claim 4, wherein the step 3) comprises:

Or

Second vibrating displacement cluster

Wherein m is the number of turns of the rotor rotating in each buffering period, m is 20, i is the number of buffering periods,

analysis of

Average value of (2)

And standard deviation of

Or

Average value of (2)

And standard deviation of

Wherein,

for the first synchronous oscillatory displacement to be the first,

for the second synchronous oscillatory displacement is carried out,

in order to displace in a first asynchronous vibration,

is a second asynchronous vibratory displacement;

(g) analyzing the frequency spectrum of the first vibration displacement cluster of the full-blade and the frequency spectrum of the second vibration displacement cluster of the full-blade according to the following methods:

Or

Second vibration displacement cluster of full blade

To pair

Or

For a short timeFourier transform to obtain a first vibration displacement cluster of the whole blade

Spectrum of

Or full-blade second vibration displacement cluster

Spectrum of

wherein:

ND is the pitch diameter of the rotor blade vibration,

(EO+ND)_Mthe frequencies of the main frequency components in the frequency spectrums of at least two full-blade first vibration displacement clusters or the frequencies of the main frequency components in the frequency spectrums of at least two full-blade second vibration displacement clusters,

the at least two full-blade first vibrational displacement clusters are corresponding vibrational displacement clusters of the leading edge of the rotor blade at least two circumferential locations in the direction of rotation,

at least two full-blade second vibrational displacement clusters are corresponding vibrational displacement clusters at least two circumferential positions of the rotor blade trailing edge in the rotational direction;

(i) based on the frequency spectrums of at least two full-blade first vibration displacement clusters or the frequency spectrums of full-blade second vibration displacement clusters and the pitch diameter of the rotor blade vibration, calculating the frequency multiplication of the rotor blade vibration according to the following formula:

EO＝(EO+ND)_M-ND；

wherein:

ND is the pitch diameter of the rotor blade vibration,

6. The method as set forth in claim 5, wherein the step 4) includes:

(j) judging whether the rotor blade generates torsional vibration or not based on the torsional angle of each rotor blade, if so, judging whether the rotor blade generates torsional vibration or not_(b,n)If not equal to 0, judging that the rotor blade generates torsional vibration;

(k) judging whether the rotor blades generate synchronous vibration or not based on the first synchronous vibration displacement and the second synchronous vibration displacement of each rotor blade, and judging that the rotor blades generate synchronous vibration if the first synchronous vibration displacement and the second synchronous vibration displacement are suddenly increased when the rotor blades rotate to a certain rotating speed;

(m) judging whether the rotor blade stalls or surges based on the first asynchronous vibration displacement, the second asynchronous vibration displacement, the frequency spectrum of the full-blade first vibration displacement cluster and the frequency spectrum of the full-blade second vibration displacement cluster of each rotor blade, if the rotor blade runs and the rotating speed of the blade tip fluctuates irregularly, the first asynchronous vibration displacement and the second asynchronous vibration displacement are increased, and non-integer frequency multiplication components appear in the frequency spectrum of the full-blade first vibration displacement cluster and the frequency spectrum of the full-blade second vibration displacement cluster, judging that the turbomachine stalls,

(n) after the stall is generated, if the first asynchronous vibration displacement and the second asynchronous vibration displacement are continuously increased, the turbine mechanical noise fluctuation is severe, the frequency spectrum of the full-blade first vibration displacement cluster and the non-integer frequency multiplication component amplitude in the frequency spectrum of the full-blade second vibration displacement cluster are increased to become a main frequency component, namely (EO + ND)_MJudging that the turbo machinery has surging if the number is non-integer;

(o) determining whether the rotor blade has flutter based on the first vibration displacement, the second vibration displacement, the torsion angle of each rotor blade and the pitch diameter of the rotor blade vibration, wherein if the rotor blade is in operation, the first vibration displacement and the second vibration displacement are increased, and the rotor blade vibration is in pitch diameter type bending and twisting coupled vibration, namely α_(b,n)If not equal to 0 and ND not equal to 0, judging that the turbo machinery generates flutter;

(p) judging whether rotor-seal rubbing or rotor thermal bending occurs based on the first vibration displacement, the second vibration displacement, the first frequency conversion and the second frequency conversion of each rotor blade, if the rotor blades operate in a low-speed non-resonance region, the first vibration displacement, the second vibration displacement, the first frequency conversion and the second frequency conversion of one or part of the rotor blades are different from the rest rotor blades, and the difference is larger along with the increase of continuous operation time, judging that the rotor-seal rubbing fault occurs in the turbomachine, and the rotor thermal bending is caused by the long-time rotor-seal rubbing, so that the differences of the first vibration displacement, the second vibration displacement, the first frequency conversion and the second frequency conversion of each rotor blade under the same working condition are larger;

(r) judging whether rotor unbalanced vibration occurs or not based on the first vibration displacement and the second vibration displacement of each rotor blade, wherein the radial vibration caused by rotor unbalance in the blade operation process can change the blade tip clearance of the rotor blade at the unbalanced position, so that the first vibration displacement and the second vibration displacement of the rotor blade at the unbalanced position are increased or reduced, and therefore if the rotor blades operate, the first vibration displacement and the second vibration displacement of a certain rotor blade are different from the first vibration displacement and the second vibration displacement of the rest rotor blades, and judging that the rotor unbalanced fault occurs in the turbomachine.

7. The method of claim 6, wherein the turbomachine is an aircraft engine or a gas turbine.

8. A diagnostic device for a turbomachine fault, said diagnostic device comprising:

measurement module (610): measuring a first arrival time of a key phase reference on the turbomachine to a first target position, a second arrival time of a leading edge of each rotor blade to a second target position, and a third arrival time of a trailing edge of each rotor blade to a third target position;

a calculation module (620): calculating a first vibrational displacement, a second vibrational displacement, a first frequency of rotation, a second frequency of rotation, and a twist angle of a rotor blade of the turbomachine based on the first time of arrival, the second time of arrival, and the third time of arrival;

analysis module (630): the system is used for analyzing the characteristics of the vibration of the rotor blades, including synchronous vibration, asynchronous vibration, frequency spectrum, pitch diameter and frequency multiplication, based on the first vibration displacement and the second vibration displacement of each rotor blade;

a judging module (640): the method is used for judging the fault type of the turbomachine based on the first rotating frequency, the second rotating frequency and the torsion angle of the rotor blade and the vibration characteristics of the rotor blade;

alarm module (650): for alarming based on the type of failure of the turbomachine.

9. The apparatus of claim 8, wherein:

the measurement module (610) comprises:

a first optical sensor (611) mounted on one side of the rotor blade drive shaft for measuring a first arrival time of the key phase reference at the first target position and providing a reference for the vibration of the rotor blade;

a second optical sensor (612) mounted on the casing corresponding to the position of the leading edge of the rotor blade for measuring a second arrival time of each of the leading edges of the rotor blades to a second target position;

a third optical sensor (613) mounted on the casing corresponding to the position of the trailing edge of the rotor blade, for measuring a third arrival time of the trailing edge of each rotor blade at a third target position;

a laser (614) for providing a light source to the first, second, third optical sensors;

an optical-to-electrical converter (615) for converting optical signals reflected by the object to be measured received by the first optical sensor, the second optical sensor and the third optical sensor into electrical signals;

a data collector (616) for collecting the electrical signal output by the photoelectric converter (615) and converting the electrical signal into a time sequence of arrival according to the level of the electrical signal;

the calculation module (620) comprises:

a first calculation module (621) for calculating a first vibrational displacement of each rotor blade based on the first and second arrival times;

a second calculation module (622) for calculating a second vibratory displacement of each rotor blade based on the first and third arrival times;

a third calculation module (623) for calculating a first rotation frequency for each rotor blade based on the second arrival time;

a fourth calculation module (624) for calculating a second rotation frequency for each rotor blade based on the third arrival time;

a fifth calculation module (625) for calculating a twist angle of each rotor blade based on the first vibrational displacement and the second vibrational displacement;

the analysis module (630) comprises:

a first analysis module (631) for analyzing the synchronous and asynchronous vibrations of each rotor blade based on the first and second vibrational displacements of each rotor blade;

a second analysis module (632) for analyzing a frequency spectrum of a full-blade first vibrational displacement cluster and a frequency spectrum of a full-blade second vibrational displacement cluster based on the first vibrational displacement or the second vibrational displacement of said each rotor blade;

a third analysis module (633) for analyzing a pitch diameter of a rotor blade vibration based on a frequency spectrum of at least two of the full-blade first vibrational displacement clusters or a frequency spectrum of a full-blade second vibrational displacement cluster;

a fourth analysis module (634) for analyzing a octave of rotor blade vibrations based on a frequency spectrum of at least two of the full-blade first vibrational displacement clusters or a frequency spectrum of a full-blade second vibrational displacement cluster, and a pitch diameter of the rotor blade vibrations;

the judging module (640) comprises:

a first determining module (641) for determining whether a torsional vibration has occurred in the rotor blade based on the torsional angle of each of the rotor blades;

a second determining module (642) for determining whether a synchronous oscillation of the rotor blade has occurred based on the first and second synchronous oscillation displacements of each rotor blade;

a third judging module (643) for judging whether asynchronous vibration of a rotor blade has occurred based on the first asynchronous vibration displacement and the second asynchronous vibration displacement of each rotor blade;

a fourth judging module (644) for judging whether a stall or surge occurs in the rotor blade based on the first asynchronous vibration displacement, the second asynchronous vibration displacement, the frequency spectrum of the full-blade first vibration displacement cluster and the frequency spectrum of the full-blade second vibration displacement cluster of each rotor blade;

a fifth determining module (645) for determining whether the rotor blade flutters based on the first vibration displacement, the second vibration displacement, the torsion angle of each rotor blade, and the pitch diameter of the rotor blade vibration;

a sixth determining module (646) for determining whether rotor-seal rub-on or rotor thermal bending has occurred based on the first vibrational displacement, the second vibrational displacement, the first frequency of rotation, and the second frequency of rotation of each of the rotor blades;

a seventh determining module (647) for determining whether a blade-casing rub impact has occurred based on the first and second rotation frequencies of each rotor blade;

an eighth determining module (648) for determining whether a rotor unbalance vibration has occurred based on the first and second vibration displacements of each rotor blade;

the alarm module (650) comprises:

a first alarm indicator light (651) for indicating whether the rotor blade is torsionally vibrated, the first alarm indicator light being on when the rotor blade is torsionally vibrated;

a second alarm indicator light (652) for indicating whether the rotor blade is vibrated synchronously, the second alarm indicator light being on when the rotor blade is vibrated synchronously;

a third warning indicator light (653) for indicating whether the rotor blade is vibrating asynchronously, the third warning indicator light being lit when the rotor blade is vibrating asynchronously;

a fourth warning indicator light (654) for indicating whether the rotor blade is stalled or surging, the fourth warning indicator light being illuminated when the rotor blade is stalled or surging;

a fifth warning indicator light (655) for indicating whether the rotor blade flutters, the fifth warning indicator light being on when the rotor blade flutters;

a sixth alarm indicator (656) for indicating whether rotor-seal rub-on or rotor thermal bowing has occurred, the sixth alarm indicator being illuminated when rotor-seal rub-on or rotor thermal bowing has occurred;

a seventh alarm indicating lamp (657) for indicating whether or not the blade-casing rub-impact occurs, the seventh alarm indicating lamp being on when the blade-casing rub-impact occurs;

and an eighth alarm lamp (658) for indicating whether or not the rotor unbalance vibration has occurred, and the eighth alarm lamp is turned on when the rotor unbalance vibration has occurred.

10. An electronic device, characterized in that the electronic device comprises a processor (1210), a memory (1220) and a bus (1230), the processor (1210) and the memory (1220) communicating via the bus (1230) when the electronic device is operating,

the memory (1220) stores machine-readable instructions executable by the processor (1210), which when executed by the processor (1210) perform performing implementing the method of any of claims 1-7.