CN115060503B - Aeroengine rotor running state evaluation method based on state information entropy - Google Patents
Aeroengine rotor running state evaluation method based on state information entropy Download PDFInfo
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Abstract
The invention discloses an aircraft engine rotor running state evaluation method based on state information entropy, which comprises the steps of firstly measuring an initial amplitude-rotating speed curve of the operation of an aircraft engine rotor; re-measuring run t b Amplitude after time-rotation speed curve; next, an amplitude-rotation speed curve A is calculated b (n) corresponding aircraft engine rotor state information entropy Z b The method comprises the steps of carrying out a first treatment on the surface of the Repeating the calculation to obtain an operation t c 、t d 、t e … amplitude-rotating speed curve and state information entropy thereof, and amplitude-rotating speed curve and state information entropy of the aero-engine when reaching the life limit moment; arranging the state information entropy values obtained at each moment on a state information entropy value-use time chart according to the use time sequence; all points are connected from small to large according to the service time, and an aeroengine rotor full life state information entropy value-service time diagram is obtained; finally, the service life of the aeroengine rotor with the same model in subsequent operation is evaluated. The invention quantitatively reflects the running state and stability of the rotor, and has actual physical significance and actual operability.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to an aero-engine rotor running state evaluation method.
Background
In the field of aeroengine fault diagnosis and life prediction, various methods based on different principles have been developed to date. In the application process, only one method is often adopted in isolation, but the problem tends to be more comprehensively reflected through multiple indexes.
Thermodynamic entropy in thermodynamics is macroscopically a state parameter, and any irreversible factor will lead to an increase in entropy. The formula is:microcosmic, is used to describe the disorder of thermal motion of molecules. The information entropy in informatics is uncertainty for describing information sources, which is proposed by shannon (C.E. Shanno) by the concept of thermodynamic entropy, and the formula is as follows: i= Σp i log 2 P i 。
As shown in FIG. 2, a P-Z diagram of the aircraft engine rotor was made by analogy with the T-S diagram in thermodynamics. Wherein, the power P is analogous to the temperature T in thermodynamics, and the state information entropy Z is analogous to the thermodynamic entropy S in thermodynamics.
The aero-engine rotor is used as a control body, is an open system, and only transmits energy with the outside without mass transmission. In an ideal reversible state, the 4-segment cycle shown in fig. 2 can be obtained when the aeronautical rotor system is in operation. The explanation is as follows:
(1) a-B. The turbine end of the rotor extracts energy from the high-temperature and high-pressure gas, and under the reversible assumption, the turbine end of the rotor is considered to be: the high temperature and high pressure gas can provide power equal to the power required by the turbine, that is, both transmit energy under the same power supply and demand condition, so the power is a certain value P 2 . In the rotor system, energy is input from the outside, and the state becomes unstable because of the increase in energy itself, so that the state information entropy increases. In summary, for stable conditions, A→B is a horizontal line.
(2) C-D. The rotor compressor end delivers energy into the low temperature and low pressure gas, under reversible assumption conditions, it is considered that: the power required by the low-temperature low-pressure gas is equal to the power provided by the gas compressor, namely, the low-temperature low-pressure gas and the gas both carry out energy transfer under the same power supply and demand condition, so that the power is a certain value P1. In the case of the rotor system, energy is output to the outside, and the state becomes stable because of the decrease in energy itself, so that the state information entropy decreases. In summary, for stable conditions, C→D is a horizontal line.
(3) And (4) B→C, D→A. The gas leaves the turbine to flow to the tail pipe and enters the air inlet channel respectively. The two-stage process considers that the rotor system is not influenced at all, so that the state information entropy of the rotor is unchanged. So are two vertical lines.
But in actual conditions is irreversible as shown in fig. 3. In practical situations, under normal working conditions, the power provided by the high-temperature and high-pressure gas energy is larger than the power required by the turbine, and other powers are used for overcoming the loss, which is the calendar of the upper half curve. Likewise, the compressor can provide more power than is required for the low temperature, low pressure gas, and other power is used to overcome losses, which is the duration of the lower curve.
Here, the thermal efficiency in the analogous thermodynamics defines the physical quantity η z The rolling friction efficiency of the bearing is overcome for the rotating shaft under the running state.
In the irreversible state, the resistance from the rolling friction of the bearing is greatly reduced because both the turbine end and the compressor end of the rotor system overcome the resistance of the power transfer process in the reversible ideal state. The method comprises the following steps:
in the reversible state, since the turbine end and the compressor end exchange equal power energy, the two ends do not need to overcome the resistance from the power transmission process, and the energy obtained by the rotating shaft is all used for overcoming the resistance from the rolling friction of the bearing, and the efficiency is the highest, and is recorded as: η (eta) Z.re . The method comprises the following steps:
from the above analysis, it is apparent that: η (eta) Z.re ＞η Z.ir . Will [1 ]]，[2]And (5) carrying into the finishing. And will flow into the rotor system 2 Recorded as positive, work W flowing out of the rotor system 1 And (3) marking as negative, and obtaining the product after finishing:
summing the infinitesimal processes of each segment, wherein:
and then the discrete process is continuous, namely:
the above formula is: analog thermodynamic clausius integral inequality at the operating state of an aircraft engine. It shows that: when any engine rotor system works in an ideal reversible cycle at two ends, the cycle integral of the ratio of the infinitesimal power transmission quantity to the supply and demand power in the power transmission is equal to 0; when the two ends are in actual irreversible circulation work, the circulation integral of the ratio of the infinitesimal power transmission quantity to the supply and demand power in the power transmission is smaller than 0.
It is obvious that the process is not limited to,the definition of entropy in thermodynamics is analogized to the definition of state quantity, which is the state entropy of the aero-engine. This is the necessity of combining the "irreversible factor in thermodynamics to cause entropy increase" to lead to the existence of the state information entropy of the aero-engine rotor.
Further analogies are made, the state information entropy flow can also be deduced, and the state information entropy is generated. The state information entropy flow is the influence on the state of the rotor of the aero-engine when power flows in and out. The entropy production of state information is the influence of irreversible conditions inside the rotor, such as friction between a shaft and a rolling bearing, friction between a rotor and a stator, and the like, on the state of the rotor.
In the invention with the application number of CN202110348056.6, a turbine rotor service life assessment and maintenance indication system is provided. The patent calculates, verifies and simulates the fatigue strength problem under various starting operation conditions of the large steam turbine generator unit rotor. The fatigue life during operation of the turbine is quantitatively calculated. By giving service advice, accurate unit life assessment and reasonable service arrangement can greatly extend the life of the turbine. Good effect is obtained. However, this patent focuses only on the temperature field stress and fatigue strength, and does not quantitatively describe the operation state of the rotor from the point of change in energy input and output to the rotor.
In the invention of the application number CN200910195881.6, a service life evaluation method of a generator rotor and a rotor guard ring is provided. The patent analyzes life damage by analyzing finite element models of temperature fields and stress fields. The service life of the generator rotor and the rotor retaining ring can be effectively estimated, and the service life assessment technology of the whole turbo generator set is further perfected. Good effect is obtained. However, this patent focuses only on the temperature field and stress field, and does not quantitatively describe the operation state of the rotor from the point of change in energy input and output to the rotor.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides an aero-engine rotor running state evaluation method based on state information entropy, which comprises the steps of firstly measuring an initial amplitude-rotating speed curve A of the aero-engine rotor running a (n); re-measuring run t b Amplitude after time-rotation speed curve; then, the point is taken and an amplitude-rotating speed curve A is calculated b (n) corresponding aircraft engine rotor state information entropy Z b The method comprises the steps of carrying out a first treatment on the surface of the Repeating the calculation to obtain an operation t c 、t d 、t e … amplitude versus speed curve A c (n)、A d (n)、A e (n) … and State information entropy Z thereof c 、Z d 、Z e And …>t e >t d >t c >t b And reach the life limit t finish Amplitude-speed curve Z of aeroengine at moment finish (n) State information entropy Z finish The method comprises the steps of carrying out a first treatment on the surface of the Arranging the state information entropy values obtained at each moment on a state information entropy value-use time chart according to the use time sequence; all points are connected from small to large according to the service time, and an aeroengine rotor full life state information entropy value-service time diagram is obtained; finally, the service life of the aeroengine rotor with the same model in subsequent operation is evaluated. The invention quantitatively reflects the running state and stability of the rotor, and has actual physical significance and actual operability.
The technical scheme adopted by the invention for solving the technical problems comprises the following steps:
step 1: measuring an initial amplitude-rotating speed curve of the operation of the aero-engine rotor;
amplitude-rotating speed curve A of aero-engine rotor accelerating from static state is obtained through measurement a (n); the amplitude-rotating speed curve A a The abscissa of (n) is the rotation speed in rpm, and the ordinate is the vibration amplitude of the rotor of the aeroengine at the corresponding rotation speed in μm; amplitude-rotation speed curve A a (n) serving as a reference for measuring the deviation of the rotor of the aero-engine from an initial state after operation;
step 2: measuring operation t of aero-engine rotor b Amplitude after time-rotation speed curve;
by measuring to obtain the running t b Amplitude of acceleration of aeroengine rotor from stationary state after time-rotational speed curve a b (n) the amplitude-rotation speed curve A b The abscissa of (n) is the rotation speed in rpm, and the ordinate is the vibration amplitude of the rotor of the aeroengine at the corresponding rotation speed in μm;
step 3: taking the points according to the following rule and calculating an amplitude-rotating speed curve A b (n) corresponding aircraft engine rotor state information entropy Z b ；
The amplitude-rotating speed curve A in the step 1 is processed a (b) Amplitude-rotation speed curve A as described in step 2 b (n) placing in an amplitude-rotation speed coordinate system;
the amplitude-rotating speed coordinate system has the vertical axis of amplitude, the unit of mu m, the horizontal axis of rotating speed and the unit of rpm; on the abscissa axis, a section [ Vmin, vmax ] for calculating the state information entropy is determined]The method comprises the steps of carrying out a first treatment on the surface of the Within this interval, s abscissa are taken in equal steps: n is n 1 ，n 2 ……n s Correspondingly, an amplitude-rotation speed curve A is obtained a (n) versus amplitude—speed curve A b Ordinate values corresponding to the s abscissas on (n): a is that a (n 1 )，A a (n 2 )…A a (n s ) A is a b (n 1 )，A b (n 2 )…A b (n s ) The method comprises the steps of carrying out a first treatment on the surface of the The error rate of the measuring instrument is recorded as w%, i A are provided b (n x ) The value x=1, 2 … i falls within the zoneM [ A ] a (n x )-A a (n x )·w％,A a (n x )+A a (n x )·w％]Within, there are s-i A b (n y ) The value y=1, 2 … s-i falls within the interval [ a ] a (n y )-A a (n y )·w％,A a (n y )+A a (n y )·w％]Outside of that; then the formula is:
calculating to obtain rotor operation t b After time, aircraft engine rotor state information entropy Z b ；
Step 4: repeating the step 2 and the step 3 to obtain the operation t of the rotor of the aero-engine c ，t d ，t e … amplitude versus speed curve A c (n)、A d (n)、A e (n) … and State information entropy Z thereof c ，Z d ，Z e … and … > t e >t d >t c >t b Reaching the life limit t finish Amplitude-rotation speed curve A of aero-engine rotor at moment finish (n) State information entropy Z finish The method comprises the steps of carrying out a first treatment on the surface of the The t is c ，t d ，t e … means that the service time is t before the rotor life of the aircraft engine is fully exhausted finish Before, the moment for calculating the state information entropy of the aero-engine at the corresponding moment;
step 5: arranging the state information entropy values obtained at each moment on a state information entropy value-use time chart according to the use time sequence;
the state information entropy value-using time chart is: the abscissa is the use time, the unit is s, the ordinate is the state information entropy value, and the unit is bit & mu m;
the point A coordinates are (t) a ，Z a ) Wherein t is a ＝0，Z a =0, which means that the working time is 0s when the aero-engine leaves the factory, and the state information entropy of the rotor of the aero-engine is 0bit at the momentμm; coordinate point A (t a ，Z a ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory b After a time, the entropy of the measured state information is Z b Coordinate point B (t b ，Z b ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory c After a time, the entropy of the measured state information is Z c Coordinate point C (t c ，Z c ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory d After a time, the entropy of the measured state information is Z d Coordinate point D (t d ，Z d ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory e After a time, the entropy of the measured state information is Z e Coordinate point E (t e ，Z e ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory finish After a time, the entropy of the measured state information is Z finish The coordinate point Finish (t finish ，Z finish ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory finish After the time, the device can not be used any more and the service life is finished;
step 6: connecting all points in the step 5 from small to large according to the service time to obtain a full life state information entropy value-service time diagram of the aero-engine rotor;
the service time chart comprises state information entropy values measured at intervals in the period from just leaving the factory to the end of the service life of the aero-engine rotor;
step 7: performing life assessment on the subsequently used aeroengine rotors of the same model by utilizing the entropy value of the whole life state information of the aeroengine, namely the use time chart, obtained in the step 6;
after the aero-engine of the same model is recorded to work for a period of time, the state entropy measured according to the methods of steps 1 and 2 isSearching for the ordinate as the full life state information entropy value of the model aeroengine obtained in the step 6, namely a using time chartThe abscissa corresponding to the time is marked +.>Then at this time, it is estimated that its time from factory use is +.>The residual life is
The beneficial effects of the invention are as follows:
the invention quantitatively describes the running state of the rotor through the angle of changing the input and output of energy to the rotor, and provides a parameter and a calculation formula of state information entropy. The state information entropy of the amplitude-rotating speed curve in the rotating speed interval is calculated to quantitatively reflect the running state and stability of the rotor compared with the state information entropy of the initial amplitude-rotating speed curve, and the state under the full rotating speed is comprehensively evaluated by focusing on a specific fault point; the invention crosses two subjects of thermodynamics and informatics, crosses the two subjects, is applied to the evaluation of the running state of the aeroengine, is a brand new angle, and has actual physical significance and actual operability.
Drawings
FIG. 1 is a flow chart of the design of the present invention.
FIG. 2 is a P-Z diagram of a rotor of an aircraft engine in an ideal state of the rotor.
Fig. 3 is a P-Z diagram of the rotor of the aircraft engine in an actual irreversible state.
FIG. 4 is a graph A of amplitude versus rotational speed measured on a test bed for a tooth coupling having a just-out fit clearance of 0mm and a fit surface roughness of 0.8 in an embodiment of the present invention a (n)。
FIG. 5 is a graph A of amplitude versus rotational speed measured on a test bed for a set-rule set-tooth coupling having a clearance of 0.01mm and a mating surface roughness of 0.8 in accordance with an embodiment of the present invention b (n)。
FIG. 6 is a graph of amplitude versus rotational speed for each set of tooth couplings obtained in step 1/2/4 of the present invention.
FIG. 7 is a graph showing the entropy of state information at each time measured in the embodiment of the present invention, which is marked on the state information entropy value-the usage time.
FIG. 8 is a graph of entropy of life-state information of a set of tooth couplings versus time for use in an embodiment of the present invention.
Fig. 9 is a schematic view of an evaluation set tooth coupling according to an embodiment of the present invention.
Detailed Description
The invention will be further described with reference to the drawings and examples.
In order to overcome the defect that the running state of the rotor is quantitatively described from the angle of change brought by energy input and output to the rotor in the prior art, the invention provides an aeroengine rotor running state evaluation method based on state information entropy. As shown in fig. 1.
Step 1: measuring an initial amplitude-rotating speed curve of the operation of the aero-engine rotor;
amplitude-rotating speed curve A of aero-engine rotor accelerating from static state is obtained through measurement a (n); the amplitude-rotating speed curve A a The abscissa of (n) is the rotation speed in rpm, and the ordinate is the vibration amplitude of the rotor of the aeroengine at the corresponding rotation speed in μm; amplitude-rotation speed curve A a (n) serving as a reference for measuring the deviation of the rotor of the aero-engine from an initial state after operation;
step 2: measured navigationAir engine rotor operation t b Amplitude after time-rotation speed curve;
by measuring to obtain the running t b Amplitude of acceleration of aeroengine rotor from stationary state after time-rotational speed curve a b (n) the amplitude-rotation speed curve A b The abscissa of (n) is the rotation speed in rpm, and the ordinate is the vibration amplitude of the rotor of the aeroengine at the corresponding rotation speed in μm;
step 3: taking the points according to the following rule and calculating an amplitude-rotating speed curve A b (n) corresponding aircraft engine rotor state information entropy Z b ；
The amplitude-rotating speed curve A in the step 1 is processed a (n) amplitude-rotation speed Curve A described in step 2 b (n) placing in an amplitude-rotation speed coordinate system;
the amplitude-rotating speed coordinate system has the vertical axis of amplitude, the unit of mu m, the horizontal axis of rotating speed and the unit of rpm; on the abscissa axis, a section [ Vmin, vmax ] for calculating the state information entropy is determined]The method comprises the steps of carrying out a first treatment on the surface of the Within this interval, s abscissa are taken in equal steps: n is n 1 ，n 2 ……n s Correspondingly, an amplitude-rotation speed curve A is obtained a (n) versus amplitude—speed curve A b Ordinate values corresponding to the s abscissas on (n): a is that a (n 1 )，A a (n 2 )…A a (n s ) A is a b (n 1 )，A b (n 2 )…A b (n s ) The method comprises the steps of carrying out a first treatment on the surface of the The error rate of the measuring instrument is recorded as w%, i A are provided b (n x ) The value x=1, 2 … i falls within the interval [ a ] a (n x )-A a (n x )·w％,A a (n x )+A a (n x )·w％]Within, there are s-i A b (n y ) The value y=1, 2 … s-i falls within the interval [ a ] a (n y )-A a (n y )·w％,A a (n y )+A a (n y )·w％]Outside of that; then the formula is:
calculating to obtain rotor operation t b After time, aircraft engine rotor state information entropy Z b ；
Step 4: repeating the step 2 and the step 3 to obtain the operation t of the rotor of the aero-engine c ，t d ，t e … amplitude versus speed curve A c (n)、A d (n)、A e (n) … and State information entropy Z thereof c ，Z d ，Z e … and … > t e >t d >t c >t b Reaching the life limit t finish Amplitude-rotation speed curve A of aero-engine rotor at moment finish (n) State information entropy Z finish The method comprises the steps of carrying out a first treatment on the surface of the The t is c ，t d ，t e … means that the service time is t before the rotor life of the aircraft engine is fully exhausted finish Previously, the moment used for calculating the state information entropy of the aero-engine at the corresponding moment. For t is as described c ，t d ，t e At the moment …, if the time interval is shorter, the more accurate the service time diagram is, the entropy value of the whole life state information of the aero-engine rotor obtained in the step 6 is;
step 5: arranging the state information entropy values obtained at each moment on a state information entropy value-use time chart according to the use time sequence;
the state information entropy value-using time chart is: the abscissa is the use time, the unit is s, the ordinate is the state information entropy value, and the unit is bit & mu m;
the point A coordinates are (t) a ，Z a ) Wherein t is a ＝0，Z a =0, which means that when the aeroengine leaves the factory, the working time is 0s, and the state information entropy of the rotor of the aeroengine is 0bit μm; coordinate point A (t a ，Z a ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory b After a time, the entropy of the measured state information is Z b Coordinate point B (t b ，Z b ) Marked in the shape ofState information entropy value-in the usage time diagram;
recording the distance t of the rotor of the aero-engine from the factory c After a time, the entropy of the measured state information is Z c Coordinate point C (t c ，Z c ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory d After a time, the entropy of the measured state information is Z d Coordinate point D (t d ，Z d ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory e After a time, the entropy of the measured state information is Z e Coordinate point E (t e ，Z e ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory finish After a time, the entropy of the measured state information is Z finish The coordinate point Finish (t finish ，Z finish ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory finish After the time, the device can not be used any more and the service life is finished;
step 6: connecting all points in the step 5 from small to large according to the service time to obtain a full life state information entropy value-service time diagram of the aero-engine rotor;
the service time chart comprises state information entropy values measured at intervals in the period from just leaving the factory to the end of the service life of the aero-engine rotor;
step 7: performing life assessment on the subsequently used aeroengine rotors of the same model by utilizing the entropy value of the whole life state information of the aeroengine, namely the use time chart, obtained in the step 6;
after the aero-engine of the same model is recorded to work for a period of time, the state entropy measured according to the methods of steps 1 and 2 isSearching for a vertical coordinate of ++according to the entropy value of the full life state information of the model aeroengine obtained in the step 6-using time diagram>The abscissa corresponding to the time is marked +.>Then at this time, it is estimated that its time from factory use is +.>The residual life is
Specific examples:
the method of the invention is verified by simulating the operation of the aircraft engine rotor by using a sleeve gear coupling in the aircraft engine rotor.
Step one: taking a certain type of sleeve gear coupler, wherein the fit clearance is 0mm, and the roughness of the fit surface is 0.8. Measuring the initial amplitude-rotation speed curve A a (n)
Taking a sleeve tooth coupler with a certain type of fit clearance of 0mm and a fit surface roughness of 0.8, and measuring to obtain an amplitude-rotating speed curve A when the sleeve tooth coupler accelerates to a certain rotating speed value from a static state a (n) the amplitude-rotation speed curve A a The abscissa of (n) is the rotation speed unit of rpm, and the ordinate is the vibration amplitude of the sleeve gear coupling at the corresponding rotation speed unit of mum. Amplitude-rotation speed curve A a (n) is used as a reference for measuring the deviation from the initial state after the sleeve gear coupler is operated for a period of time. Shown in fig. 4.
Step two: taking the same type of sleeve gear coupler, measuring the amplitude-rotating speed curve A, wherein the fit clearance is 0.01mm, the roughness of the fit surface is 0.8 b (n) and calculating the state information entropy Z b 。
Taking a sleeve tooth coupler with the same type and 0.01mm of fit clearance and 0.8 of roughness of the fit surface, and obtaining the sleeve tooth coupler through measurementAmplitude-speed curve A when sleeve gear coupling is accelerated from stationary state to certain speed value after running for a period of time b (n) the amplitude-rotation speed curve A b The abscissa of (n) is the rotation speed unit of rpm, and the ordinate is the vibration amplitude of the sleeve gear coupling at the corresponding rotation speed unit of mum. As shown in fig. 5.
Step three: taking points according to a certain rule and calculating an amplitude-rotating speed curve A b (n) corresponding set-tooth coupling State information entropy Z b
Step one, the amplitude-rotating speed curve A a (n) and step two, the amplitude-rotation speed curve A b (n) is placed in an amplitude-rotation speed coordinate system. The amplitude-rotating speed coordinate system has the vertical axis of amplitude, the unit of mu m, the horizontal axis of rotating speed and the unit of rpm. On the abscissa axis, an interval [1600,4000 ] for calculating the state information entropy is determined]. In this interval, 481 abscissas are taken at equal step size 5: n is n 1 ＝1600，n 2 ＝1605，n 3 ＝1610……n 481 =4000, correspondingly, an amplitude-rotation speed curve a is obtained a (n) versus amplitude—speed curve A b Ordinate values corresponding to the s abscissas on (n): a is that a (n 1 )，A a (n 2 )…A a (n s ) A is a b (n 1 )，A b (n 2 )…A b (n s ). The error rate of the measuring instrument was noted to be 2%. Then there are 8A b (n x ) Values, x=1, 2 … 7,8, fall within interval [ a a (n x )-A a (n x )·2％,A a (n x )+A a (n x )·2％]Within 473A b (n y ) Values of y=1, 2 … 473 falling within interval a a (n y )-A a (n y )·2％,A a (n y )+A a (n y )·2％]Outside of that. Then the calculation is made by the formula:
step four: and continuously adopting the sleeve gear couplings with different fit clearances and roughness of the fit surfaces to simulate the running state of the aero-engine rotor along with the change of time. And repeating the second and third steps to obtain amplitude-rotation speed curve A c (n)，A finish (n); and calculating state information entropy: z is Z c ,Z finish ,。
Taking a sleeve tooth coupler with the fit clearance of 0.01mm and the roughness of the fit surface of 1.6 in the same model, and repeating the second and third steps. Obtaining an amplitude rotation speed curve A c (n) calculating Z c ＝114.0507bit·μm。
Taking a sleeve tooth coupler with the fit clearance of 0.02mm and the roughness of the fit surface of 1.6 in the same model, and repeating the second and third steps. Obtaining an amplitude rotation speed curve A finish (n) calculating Z finish ＝298.2765bit·μm。
At this time, it is considered that when the fit clearance of the type sleeve rule coupler is 0.02mm and the roughness of the fit surface is 1.6, the sleeve rule coupler cannot be used continuously, and the service life of the sleeve rule coupler is fully exhausted.
The amplitude-rotating speed curves obtained in the first step, the second step and the fourth step are shown in figure 6.
Step five: the state information entropy values obtained at each moment are arranged on a state information entropy value-using time chart according to the using time sequence
The state information entropy value-using time chart is: the abscissa is the time of use, the unit is s, the ordinate is the state information entropy, and the unit is bit·μm.
The point A coordinates are (t) a ，Z a ). Wherein t is a ＝0，Z a =0. The working time is 0s when the set of tooth couplings are just shipped, and the state information entropy is 0bit mu m. Coordinate point A (t a ，Z a ) Marked in the state information entropy value-use time diagram.
Recording the distance t of the model sleeve gear coupling from factory b Then, the measured state information entropy value is Z b Coordinate point B (t b ，Z b ) Marked in the state information entropy value-use time diagram.
Recording the distance t of the model sleeve gear coupling from factory c Then, the entropy of the measured state information is Z c Coordinate point C (t c ，Z c ) Marked in the state information entropy value-use time diagram.
Recording the distance t of the model sleeve gear coupling from factory finish Then, the entropy of the measured state information is Z finish The coordinate point Finish (t finish ，Z finish ) Marked in the state information entropy value-use time diagram.
As shown in fig. 7.
Step six: the fifth step is connected according to the service time from small to large to obtain the full life state information entropy value-service time diagram of the type of sleeve-tooth coupler
The obtained diagram is shown in FIG. 8
Step seven: and D, evaluating the life of the subsequently used sleeve gear coupler of the model by utilizing the information entropy value of the full life state of the sleeve gear coupler of the model, namely the use time chart.
After the same set of tooth couplings of the model are recorded to work for a period of time, the entropy of the states measured according to the first step and the second step isSearching for a ordinate of ++according to the entropy value of the full life state information of the model sleeve ruler obtained in the step six, namely the using time chart>The abscissa corresponding to the time is marked +.>As shown in fig. 9. Then at this time, it can be estimated that its time from factory use is +.>The residual life is +.>
Claims (1)
1. An aeroengine rotor running state evaluation method based on state information entropy is characterized by comprising the following steps:
step 1: measuring an initial amplitude-rotating speed curve of the operation of the aero-engine rotor;
amplitude-rotating speed curve A of aero-engine rotor accelerating from static state is obtained through measurement a (n); the amplitude-rotating speed curve A a The abscissa of (n) is the rotation speed in rpm, and the ordinate is the vibration amplitude of the rotor of the aeroengine at the corresponding rotation speed in μm; amplitude-rotation speed curve A a (n) serving as a reference for measuring the deviation of the rotor of the aero-engine from an initial state after operation;
step 2: measuring operation t of aero-engine rotor b Amplitude after time-rotation speed curve;
by measuring to obtain the running t b Amplitude of acceleration of aeroengine rotor from stationary state after time-rotational speed curve a b (n) the amplitude-rotation speed curve A b The abscissa of (n) is the rotation speed in rpm, and the ordinate is the vibration amplitude of the rotor of the aeroengine at the corresponding rotation speed in μm;
step 3: taking the points according to the following rule and calculating an amplitude-rotating speed curve A b (n) corresponding aircraft engine rotor state information entropy Z b ；
The amplitude-rotating speed curve A in the step 1 is processed a (n) amplitude-rotation speed Curve A described in step 2 b (n) placing in an amplitude-rotation speed coordinate system;
the amplitude-rotating speed coordinate system has the vertical axis of amplitude, the unit of mu m, the horizontal axis of rotating speed and the unit of rpm; on the abscissa axis, a section [ Vmin, vmax ] for calculating the state information entropy is determined]The method comprises the steps of carrying out a first treatment on the surface of the Within this interval, s abscissa are taken in equal steps: n is n 1 ，n 2 ......n s Correspondingly, an amplitude-rotation speed curve A is obtained a (n) vibrationAmplitude-rotation speed curve A b Ordinate values corresponding to the s abscissas on (n): a is that a (n 1 )，A a (n 2 )...A a (n s ) A is a b (n 1 )，A b (n 2 )...A b (n s ) The method comprises the steps of carrying out a first treatment on the surface of the The error rate of the measuring instrument is recorded as w%, i A are provided b (n x ) The value of the sum of the values, x=1, 2. I. drop in interval [ A ] a (n x )-A a (n x )·w％，A a (n x )+A a (n x )·w％]Within, there are s-i A b (n y ) Values, y=1, 2..s-i fall within interval [ a a (n y )-A a (n y )·w％，A a (n y )+A a (n y )·w％]Outside of that; then the formula is:
calculating to obtain rotor operation t b After time, aircraft engine rotor state information entropy Z b ；
Step 4: repeating the step 2 and the step 3 to obtain the operation t of the rotor of the aero-engine c ，t d ，t e .. amplitude versus speed curve A c (n)、A d (n)、A e (n.) state information entropy Z c ，Z d ，Z e .. and.> t e ＞t d ＞t c ＞t b Reaching the life limit t finish Amplitude-rotation speed curve A of aero-engine rotor at moment finish (n) State information entropy Z finish The method comprises the steps of carrying out a first treatment on the surface of the The t is c ，t d ，t e .. it is meant that the life of the rotor of the aircraft engine is fully exhausted, i.e. for a time t finish Before, the moment for calculating the state information entropy of the aero-engine at the corresponding moment;
step 5: arranging the state information entropy values obtained at each moment on a state information entropy value-use time chart according to the use time sequence;
the state information entropy value-using time chart is: the abscissa is the use time, the unit is s, the ordinate is the state information entropy value, and the unit is bit & mu m;
the point A coordinates are (t) a ，Z a ) Wherein t is a ＝0，Z a =0, which means that when the aeroengine leaves the factory, the working time is 0s, and the state information entropy of the rotor of the aeroengine is 0bit μm; coordinate point A (t a ，Z a ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory b After a time, the entropy of the measured state information is Z b Coordinate point B (t b ，Z b ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory c After a time, the entropy of the measured state information is Z c Coordinate point C (t c ，Z c ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory d After a time, the entropy of the measured state information is Z d Coordinate point D (t d ，Z d ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory e After a time, the entropy of the measured state information is Z e Coordinate point E (t e ，Z e ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory finish After a time, the entropy of the measured state information is Z finish The coordinate point Finish (t finish ，Z finish ) Marked in state information entropy value-use time chart;
recording the distance t of the rotor of the aero-engine from the factory finish After the time, the device can not be used any more and the service life is finished;
step 6: connecting all points in the step 5 from small to large according to the service time to obtain a full life state information entropy value-service time diagram of the aero-engine rotor;
the service time chart comprises state information entropy values measured at intervals in the period from just leaving the factory to the end of the service life of the aero-engine rotor;
step 7: performing life assessment on the subsequently used aeroengine rotors of the same model by utilizing the entropy value of the whole life state information of the aeroengine, namely the use time chart, obtained in the step 6;
after the aero-engine of the same model is recorded to work for a period of time, the state entropy measured according to the methods of steps 1 and 2 isSearching for a vertical coordinate of ++according to the entropy value of the full life state information of the model aeroengine obtained in the step 6-using time diagram>The abscissa corresponding to the time is marked +.>Then at this time, it is estimated that its time from factory use is +.>The residual life is +.>
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