CN106872172A - The method for real time discriminating and system of Aero Engine Testing security parameter monitoring - Google Patents
The method for real time discriminating and system of Aero Engine Testing security parameter monitoring Download PDFInfo
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The present invention relates to the method for real time discriminating and system of a kind of monitoring of Aero Engine Testing security parameter, the method is：By the related key parameter of engine health, a multidimensional stable state rating data table is set up；By stable state rating data table, the rated value of security parameter in real-time update steady-state process；On the basis of stable state rating data table, upper safety limit and lower limit of each parameter under respective conditions are determined；Provide the actual time safety parameter upper limit of transient process and the value rule of lower limit；The engine test for carrying out multi-parameter association analysis differentiates safely；Carry out the TCH test channel fault distinguishing that single measuring point transfinites；The rated value of security parameter in transient process is calculated in real time；Iteration updates the two-dimentional ratings data table of security parameter in transient process.The system is built table function module, transition state security parameter and builds table function module and in real time monitoring warning function module including stable state security parameter.The present invention effectively can be alarmed or pre-alarm aero-engine failure.
Description
Technical field
The present invention relates to Engine Block Test technical field, and in particular to a kind of Aero Engine Testing security parameter monitoring
Method for real time discriminating and system.
Background technology
Overall test is a significant process of reseach of engine.Overall test has various sorting techniques.By whole machine development
Stage can be divided into：Principle prototype experiment, verification machine experiment, the experiment of model machine etc..In process of the test, both examined including ground
Experiment, and including HIGHER ALTITUDE TEST FACILITY performance adjustment and certification test.But, due to experiment in many uncertainties, particularly in original
To many characteristics of engine be not in reason prototype design, before engine test completely can with digital simulation, many intensity,
Stress, transmission, control problem may not expose fully also, so ensureing that engine health is extremely difficult in experiment
's.And a principle prototype, R＆D costs are huge, once experiment is damaged, loss is also heavy, so, it is various test into
Ensure by the safety of spreadsheet engine it is very meaningful while row.
The content of the invention
For problem above, the present invention proposes one kind and is skillfully constructed, rationally, can be used for engines ground or altitude simulation
Engine failure is alarmed or pre-alarm in experiment, and then to being suspected to be that failure section, fault parameter are warned to test personnel,
Cause the attention of test personnel early, it is ensured that the real-time of Aero Engine Testing security parameter monitoring of tested engine health is sentenced
Other method and system.
Technical scheme is as follows：
The method for real time discriminating of above-mentioned Aero Engine Testing security parameter monitoring, idiographic flow is：(1) by engine
Safety-related key parameter, sets up a multidimensional stable state rating data table；(2) by stable state rating data table, real-time update is steady
The rated value of security parameter during state；(3) on the basis of stable state rating data table, determine each parameter in respective conditions
Under upper safety limit and lower limit；(4) the actual time safety parameter upper limit of transient process and the value rule of lower limit are given；(5)
The engine test for carrying out multi-parameter association analysis differentiates safely；(6) the TCH test channel fault distinguishing that single measuring point transfinites is carried out.
The method for real time discriminating of the Aero Engine Testing security parameter monitoring, wherein, step (5) the engine examination
Test safety differentiation be specifically：According to the security parameter upper and lower bound that given or calculating determines, real time discriminating test engine
Whether unsafe working condition is entered.
The method for real time discriminating of the Aero Engine Testing security parameter monitoring, wherein：Step (5) the engine examination
Test safety and differentiate it is that is, same section based on many reference amounts correlating method, when there are two or more different type abnormal parameters
Or same class parameter is when all transfiniting, abnormal section and possible failure are reported at once.
The method for real time discriminating of the Aero Engine Testing security parameter monitoring, wherein, step (6) the list measuring point surpasses
The TCH test channel fault distinguishing of limit is specifically：In same section, multiple measuring points of identical parameter, if measuring point value transfinites,
Also there is measuring point in safety limit, association parameter is without exception, then report the Measurement channel failure of the measurement point that transfinites.
The method for real time discriminating of the Aero Engine Testing security parameter monitoring, wherein：Many stability maintenances in the step (1)
The mainly user's especially care such as including inlet temperature, inlet pressure, environmental pressure, section, rated speed of state rating data table
Key variables and its rated value.
The method for real time discriminating of the Aero Engine Testing security parameter monitoring, wherein：The value of the step (4) is
The rated value of security parameter in transient process as obtained by calculating in real time.
A kind of real time discriminating system of Aero Engine Testing security parameter monitoring, is based on described aero-engine examination
The method for real time discriminating of security parameter monitoring is tested, the system builds table function module, transition state safety including stable state security parameter
Parameter builds table function module and in real time monitoring warning function module；The stable state security parameter is built table function module and is for
The key variables that user is especially concerned about, set up its parameter value in nominal limit, for the steady of monitoring warning function in real time
State differentiates safely；The transition state security parameter builds the security parameter that table function module is for the operation of engine transition state
Key parameter values are set up, the transition state for monitoring warning function in real time differentiates safely；The real-time monitoring warning function module
It is experimental safe monitoring, real time discriminating, the alarm for being run to stable state or transition state in process of the test.
The real time discriminating system of the Aero Engine Testing security parameter monitoring, wherein, the stable state security parameter is built
The operational process of table function module is：Give table number first, be then input into the running state parameter of engine, then to uniform section or
Unit, recently enters the warning bound and failure bound of all monitored parameter and correspondence parameter on section.
The real time discriminating system of the Aero Engine Testing security parameter monitoring, wherein, the transition state security parameter
The operational process for building table function module is：When running first, each crucial running state parameter a from stable state is given
To the warning bound and failure bound of another stable state, warning bound or failure bound are one on rated value
Percentage；In running, if be not reaching to alert bound and failure bound, although or reach warning bound and therefore
Hinder bound but confirm to be judged parameter safety by button, then by iterative calculation, continuous renewal is judged the specified of parameter
Value.
The real time discriminating system of the Aero Engine Testing security parameter monitoring, wherein, the real-time monitoring alarm work(
The operational process of energy module includes that the transition state flow of the steady-state flow of monitoring in real time and real-time monitoring, i.e. program enter prison in real time
After visual alarm function, process selecting is carried out first, judge whether to monitor flow in real time into steady state test, if it is, performing reality
When the steady-state flow that monitors, if it is not, into the transition state flow of real-time monitoring；The steady-state flow of the real-time monitoring is by steady
The measured value of state security parameter directly compares with the rated value in Steady-state Parameters table and provides judgement；The transition state of the real-time monitoring
Flow by transition state security parameter measured value with calculate rated value be compared, with realize whether safety differentiation, while
The rated value of calculating is iterated by the rule for giving, and eventually forms ratings data table, is matched by tables of data.
The real time discriminating system of the Aero Engine Testing security parameter monitoring, wherein, the stable state security parameter is sentenced
The update method of the rated value of security parameter is judged in not is：New rated value is the something lost of current nominal value and current nominal value
The product of the factor is passed, the product of 1 filter value for subtracting data measured before this genic difference and current time is added.
The real time discriminating system of the Aero Engine Testing security parameter monitoring, wherein, the transition of the real-time monitoring
By the update method of the ratings data table of comparison variable in state flow：After being judged as normal by the measured value of comparison variable,
Update by the two-dimentional ratings data table of comparison variable；The current nominal value of reference variable is calculated first, and current nominal value is to work as
The smothing filtering of the multiple measured values before preceding measured value；Then, by the current nominal value of reference variable, two-dimentional ratings data
Three pairs of reference variables in table near reference variable current nominal value value with by the data of comparison variable to come calculate by than
Compared with the calculating rated value of variable；Finally, existed by comparison variable to calculate by calculating rated value, gene, original rated value
With particular reference to the rated value under conditions of variate-value, table is updated the data.
The real time discriminating system of the Aero Engine Testing security parameter monitoring, wherein, the transition state security parameter
It is by the choosing method of the rated value of comparison variable in differentiation：Transition state is by the current nominal value of comparison variable by reference variable
Initial value and stop value, inserted by linear by the current measured value of the initial value and stop value of comparison variable and reference variable
Value is calculated and obtained.
Beneficial effect：
The method for real time discriminating reasonable idea of Aero Engine Testing security parameter of the present invention monitoring, ingenious, it is according to quilt
The state of test engine and monitored parameter, can automatically differentiate whether engine is in a safe condition；Simultaneously both can be with
For the monitoring of transition state, it is also possible to for stable state monitoring, monitored parameter can be gas path parameter, oil circuit parameter, vibration ginseng
All kinds of parameters such as number, stress parameters, surge parameter.
The real time discriminating system structure design of Aero Engine Testing security parameter monitoring of the present invention is simple, reasonable, can use
In the various experiments of aero-engine, can particularly be applied in aero-engine develops early test security monitoring, such as
The principle prototype development stage；The data obtained in experimentation also have the latent of the state of health monitoring after being applied to engine installation
In value.As Aero Engine Testing security parameter of the present invention monitor real time discriminating system produced by long-term use process
The rated value of the security parameter of middle formation, it may also be used in the related application of engine condition maintenarnce；Maximum is used with simple most
Small value monitoring or segmentation monitoring are compared, and are had obvious benefits.
Brief description of the drawings
Fig. 1 is the structured flowchart of the real time discriminating system of Aero Engine Testing security parameter monitoring of the present invention；
Fig. 2 is that the stable state security parameter of the real time discriminating system of Aero Engine Testing security parameter monitoring of the present invention builds table
The operational flow diagram of functional module；
Fig. 3 is that the transition state security parameter of the real time discriminating system of Aero Engine Testing security parameter monitoring of the present invention is built
The operational flow diagram of table function module；
Fig. 4 is the real-time monitoring warning function of the real time discriminating system of Aero Engine Testing security parameter monitoring of the present invention
The operational flow diagram of module；
Fig. 5 is the real-time monitoring warning function of the real time discriminating system of Aero Engine Testing security parameter monitoring of the present invention
The steady-state flow figure of module operational process；
Fig. 6 is the real-time monitoring warning function of the real time discriminating system of Aero Engine Testing security parameter monitoring of the present invention
The transition state flow chart of module operational process.
Specific embodiment
The method for real time discriminating of Aero Engine Testing security parameter of the present invention monitoring, idiographic flow is：
S010, the key parameter by engine health correlation, set up a multidimensional stable state rating data table；The multidimensional stable state
Rating data table is including inlet temperature, inlet pressure, environmental pressure, section, rated speed, variable, rated value etc..
S020, by rating data table, according to certain computational methods, the specified of security parameter in transient process is calculated in real time
Value；
S030, on the basis of stable state rating data table, determine upper safety limit of each parameter under respective conditions and
Lower limit；
The value rule of S040, the actual time safety parameter upper limit for providing transient process and lower limit, this value is by reality
When calculate obtained by transient process in security parameter rated value.
S050, the engine test of multi-parameter association analysis differentiate safely, i.e., according to the safety ginseng for giving or calculating determines
Whether number upper and lower bound, real time discriminating test engine enters unsafe working condition；Differentiate based on many reference amounts association
Method, i.e., same section, when thering is two or more different type abnormal parameters or same class parameter all to transfinite, at once
The abnormal section of report and possible failure.
The TCH test channel fault distinguishing that S060, single measuring point transfinite, i.e., in same section, multiple measuring points of identical parameter,
If measuring point value transfinites, also there is measuring point in safety limit, association parameter is without exception, then report the Measurement channel of the measurement point that transfinites
Failure.
The real time discriminating system of Aero Engine Testing security parameter monitoring of the present invention, it is based on above-mentioned aero-engine examination
The method for real time discriminating of security parameter monitoring is tested, is a real-time automatic discrimination system for experimental safe, the foundation of differentiation is steady
State security parameter table and transition state security parameter table, it can be that any one thinks have closely to experimental safe to be judged to other parameter
The parameter of influence.
As shown in figure 1, the real time discriminating system of Aero Engine Testing security parameter monitoring of the present invention includes stable state safety
Parameter is built table function module 1, transition state security parameter and builds table function module 2 and in real time monitoring warning function module 3.
The stable state security parameter builds table function module 1 and acts on key variables (such as compressor for being directed to user and being especially concerned about
Inlet pressure, compressor delivery pressure, combustor inlet temperature, combustor exit temperature etc.), set up it in nominal stable state (such as
The steady operational status such as slow train, 85% rotating speed, first point of performance) condition parameter value, in real time monitoring warning function it is steady
State differentiates safely.Because experiment is made up of multiple stable states and multiple transition state processes of engine, therefore, the stable state is joined safely
Number builds table function module 1 and transition state security parameter builds table function module 2 and can set up the peace of different stable states or different transition states
Population parameter discrimination standard, different stable states or different transition state processes are distinguished with different table numbers, for the ease of identification, are considered as
It is different with the naming method of transition state table number to stable state, to show difference.
As shown in Fig. 2 the operational process that the stable state security parameter builds table function module 1 is：Table number is given first, it is then defeated
Enter the running state parameter of engine parameter, such as relative rotation speed, intake air temperature, admission pressure, environmental pressure, then given section
Face, recently enters the warning bound and failure bound of all monitored parameter and correspondence parameter on section.Warning is upper and lower
Limit is the value for reminding laboratory technician to note, when the measured value of monitored parameter is more than the warning upper limit or less than warning lower limit,
Laboratory technician should arouse attention, and carefully observe its change.Once the measured value of monitored parameter is more than fail high threshold or is less than
During failure lower limit, then explanation is judged the scope that parameter has reached failure.
The effect that the transition state security parameter builds table function module 2 is directed to the operation of engine transition state (i.e.：It is steady from one
State to another stable state process be transition state operation) security parameter set up key parameter values, in real time monitoring alarm work(
The transition state of energy differentiates safely.
As shown in figure 3, the operational process that the transition state security parameter builds table function module 2 is：When operation first, give
Fixed warning bound and failure bound of each crucial running state parameter from a stable state to another stable state, this
Warning bound and failure bound may come from calculated value or empirical value.Warning bound or failure bound are a passes
In the percentage of rated value.Initial rated value is obtained by calculating, or is given by a formula.During actual tests,
If reaching warning bound or failure bound, interface is indicated just to show warning or failure, and coordinate audible alarm.Ran
Cheng Zhong, if be not reaching to alert bound and failure bound, although or reach warning bound and failure bound
Operating personnel confirm to be judged parameter safety by button, then by iterative calculation, constantly update the rated value of this parameter.This
Iteration is planted, certain model or certain rated value of engine can be caused with the accumulation of run time, it is more and more accurate to become.
The effect of the real-time monitoring warning function module 3 is the aviation run to stable state or transition state in process of the test
Engine carries out experimental safe monitoring, real time discriminating, alarm announcement or report failure.
As shown in figure 4, the operational process of the real-time monitoring warning function module 3 includes the steady-state flow and reality of monitoring in real time
When the transition state flow that monitors.The operational process of the real-time monitoring warning function module 3 is：Program enters the work(of monitoring alarm in real time
After energy, sub-process selection is carried out first, judge whether to monitor flow in real time into steady state test；If it is, performing shown in Fig. 5
Stable state monitors sub-process in real time；If it is not, the transition state shown in Fig. 6 monitors sub-process in real time.The stable state for monitoring in real time
Flow is directly compared with the set-point in Steady-state Parameters table by the measured value of security parameter and provides judgement；The transition state for monitoring in real time
Flow by transition state parameter measured value with calculate rated value be compared, with realize whether safety differentiation；Calculate simultaneously
Rated value by give rule be iterated, eventually form ratings data table, matched by tables of data.
As shown in figure 5, the steady-state flow of the real-time monitoring warning function module 3 is specially：Program is pacified in real time into stable state
After full monitoring program, first according to given security parameter table number, security parameter table is read in, as the foundation of real-time judge.Connect
The section number for reading in engine measuring parameter, then the current measured value for reading in next variable.Then stored with parameter list
Security parameter rated value be compared, judge whether in warning limit.If in warning limit, illustrating present engine stable state
Parameter value is judged during operation normal, just records normal, continued executing with；If beyond warning limit, then judging that the measured value is
It is no to have reached failure limit.If having reached failure limit, failure is recorded, then proceed to perform；If being not reaching to failure limit, just remember
Record warning, then proceedes to perform.After completion is judged the whether normal judgement of parameter, measured value, result deposit is differentiated, then change
Generation calculating is judged the rated value of parameter and deposits.
It is judged the rated value x of security parameter iciIterative calculation method it is as follows：
xci=α x'ci+(1-α)mci(1)；
Wherein, xci：It is judged the current nominal value of security parameter i；x'ci：It is judged the previous volume of security parameter i
Definite value；α：The gene of the previous rated value of security parameter i is judged, α values are between 0~1.The obtaining value method of α
Should consider by the tested number of times of spreadsheet engine, for the engine for just starting experiment, α values can be with smaller；
With the increase of test number (TN), α values can gradually increase.mci：(n- before the current time of the security parameter i being judged
1) filter value of individual data, mciCalculated by formula (2) and obtained：
mci=w1xi,0+w2xi,-1+…+wnxi,-(n-1)(2)；
Wherein, xi,0、xi,-1、……、xi,-(n-1)It is respectively the current measured value for being judged security parameter i, current measured value
Previous measured value ..., (n-1) secondary measured value before current measured value；w1、w2、……、wnIt is the weight vector of filtering,
They meet relational expression (3)：
w1+w2+…+wn=1 (3)；
Next, it is judged that whether the measured value of all parameters in the section has all carried out security judgement.If also have joined
Number does not carry out security judgement, then return, and continues to read the current measured value of next variable, repeats aforementioned process；If should
The all of parameter in section is completed security judgement, then into next step.Whether next step is to judge the section
There are two class above parameters or the measured value of a certain class parameter multiple measuring point to reach more than warning limit.If it is, illustrating the section
Measured value have security threat, it is necessary to alarm or stop engine test；If it is not, explanation is measurement or the biography of certain parameter
Sensor is faulty, alarm sensor failure.After completing the step, then judge whether that all sections are completed judgement,
If also section does not complete, return, read in next section, continue to judge；If all sections all judge to complete, enter
Enter next step.Determine whether that key-press input requirement changes trystate now, i.e.,：It is required that become transition state by steady state test trying
Test.If key-press input, turn transition state and monitor sub-process in real time；If it did not, judge whether to continue to test, if it is confirmed that after
Continuous experiment, returns and reads in next section, continues to judge.If input button requirement does not continue to experiment, EP (end of program).
As shown in fig. 6, the transition state flow of the real-time monitoring warning function module 3 is specially：Transition state peace is read in first
Population parameter table number, then read in the current measured value of reference variable；Then judge reference variable whether beyond specified initial value, termination
The limits value of value, or the rate of change of reference variable exceeds limitation；The rate of change of reference variable refers to the variable quantity of reference variable
With the ratio of transformation period, it is whether too fast (in fact, rotating speed is exactly in aero-engine for weighing the change of value of reference variable
Into latter conventional reference variable of idling rating).If it is, report reference variable failure, asks to stop experiment, wait is pressed
Key confirms to stop experiment；If it is not, the current measured value of reference variable of just depositing, rate of change, differentiation result.If button is true
Stopping experiment, system are recognized it is confirmed that stopping shutting down procedure operation after testing；If button does not confirm to stop experiment, system is also returned
Current measured value, rate of change, the workflow position of differentiation result of storage reference variable are returned to, corresponding actions are completed, continued executing with.
Then read specified initial value, the stop value of next variable, reference is then searched in transition state security parameter table
The rated value of the corresponding variable under variable currency.If using for the first time, rated value is in transition state security parameter table
With formula give, the current measured value of reference variable is brought into and is calculated.Because the rated value for storing variable is with two-dimensional data table
Mode store, and the value of this tables of data is always limited, thus carry out measured value compare with rated value with it is specified
Skill is needed during the iterative calculation of value.
Search the method for the rated value for comparing：Looked into two-dimentional ratings data table by the measured value of reference variable
Table, is found at the value of reference variable in bivariate table, and interpolation calculation is calculated by the rated value of comparison variable with formula (4)
By the rated value x of comparison variable xc：
Wherein, st：The current measured value of reference variable s；sH、sL：The current measured value s of reference variabletBetween two-dimentional rated value
Two value s of reference variable in tables of dataHAnd sLBetween, sHIt is that big value, sLIt is that small value；xH、xLRespectively quilt
It is s that comparison variable x corresponds to reference variable in two-dimentional ratings data tableHAnd sLUnder rated value.
By by the rated value of comparison variable and warning bound, the ratio of failure bound, calculating warning bound, failure
The value of bound.Read, by the measured value of comparison variable, then to carry out the judgement of warning limit again.If measured value is in warning limit,
Illustrate that measured value is normal, engine is safe, and record is normal；If measured value is not in warning limit, then judges measured value
Whether in failure limit.If measured value illustrates measured value beyond warning limit in failure limit, but is also not reaching to report
The degree of failure, at this time just record is alerted；If measured value in failure limit, does not illustrate that measured value has reached report failure
Degree, failure need to be recorded.
, it is necessary to iterate to calculate after normal and normal record is judged as by the measured value of comparison variable, two dimension is updated specified
Value in Value Data table.Calculate and renewal is divided into two steps：
The first step, the calculating of reference variable current nominal value.Found with the current measured value smothing filtering of reference variable
The rated value of the reference variable being updated.The reference variable that acquisition is updated currently calculates rated value scMethod be：
sc=g1s0+g2s-1+…+gns-(n-1)(5)；
Wherein, sc：The current calculating rated value of reference variable s；s0、s-1、……、s-(n-1)：It is respectively reference variable s
First measured value before current measured value, current measured value ..., (n-1) the individual measured value before current measured value.
If measured value number is not enough before, can be replaced with the measured value at moment nearby.g1、g2、……、gn：It is respectively s0、
s-1、……、s-(n-1)Weight vector, and meet：
g1+g2+…+gn=1 (6)；
Second step, renewal is judged the rated value of variable.If counted scJoin in two-dimentional rated value parameter list
Examine the s of variable sLWith sHBetween, sHIt is that big value, sLIt is that small value, s'LIt is to compare sLThat smaller value.x'L、xL、
xHIt is respectively that to correspond to reference variable in two-dimentional rated value parameter list be s'L、sL、sHWhen the value by comparison variable, xtIt is current
Measured value, then update sLCorresponding rated value xL.First by (s' during renewalL,x'L)、(sc,xt)、(sH,xH) three points set up
Equation, it is s to be calculated in input by formula (7)LWhen output xLt：
Then rated value x is calculatedLRenewal rated value xLnew：
xLnew=β xL+(1-β)·xLt(8)；
Wherein, β is the gene of rated value.Then x is usedLnewInstead of original xLStore two-dimentional ratings data table
In.
Ensuing processing procedure, it is similar to the respective handling process in stable state monitoring sub-process, repeat no more.
All sections all recycle ratios more once after, set engine whether the judgement of conversion operation state, i.e.,
Whether judge the running status of engine will be transformed into stable state by transition state.
It is the method for real time discriminating reasonable idea of Aero Engine Testing security parameter of the present invention monitoring, ingenious, can both use
In the monitoring of transition state, it is also possible to for stable state monitoring；Monitored parameter can be gas path parameter, oil circuit parameter, vibration parameters,
All kinds of parameters such as stress parameters, surge parameter.
The real time discriminating system structure design of Aero Engine Testing security parameter monitoring of the present invention is simple, reasonable, and it can
According to by the state of test engine and monitored parameter, can automatically differentiate whether engine is in a safe condition.
Claims (13)
1. the method for real time discriminating of a kind of Aero Engine Testing security parameter monitoring, it is characterised in that idiographic flow is：
(1) by the key parameter that engine health is related, a multidimensional stable state rating data table is set up；
(2) by stable state rating data table, the rated value of security parameter in real-time update steady-state process；
(3) on the basis of stable state rating data table, upper safety limit and lower limit of each parameter under respective conditions are determined；
(4) the actual time safety parameter upper limit of transient process and the value rule of lower limit are given；
(5) engine test for carrying out multi-parameter association analysis differentiates safely；
(6) the TCH test channel fault distinguishing that single measuring point transfinites is carried out.
2. the method for real time discriminating that Aero Engine Testing security parameter as claimed in claim 1 is monitored, it is characterised in that institute
State step (5) engine test safely differentiate be specifically：It is real according to the security parameter upper and lower bound that given or calculating determines
When differentiate test engine whether enter unsafe working condition.
3. the method for real time discriminating that Aero Engine Testing security parameter as claimed in claim 1 is monitored, it is characterised in that:Institute
State step (5) engine test and differentiate it is that is, same section based on many reference amounts correlating method safely, when there are two or more
When different type abnormal parameters or same class parameter all transfinite, abnormal section and possible failure are reported at once.
4. the method for real time discriminating that Aero Engine Testing security parameter as claimed in claim 1 is monitored, it is characterised in that institute
Stating step (6) the list TCH test channel fault distinguishing that transfinites of measuring point is specifically：In same section, multiple measuring points of identical parameter,
If measuring point value transfinites, also there is measuring point in safety limit, association parameter is without exception, then report the Measurement channel of the measurement point that transfinites
Failure.
5. the method for real time discriminating that Aero Engine Testing security parameter as claimed in claim 1 is monitored, it is characterised in that：Institute
Multidimensional stable state rating data table mainly includes inlet temperature, inlet pressure, environmental pressure, section, rated speed in stating step (1)
Deng key variables and its rated value that user is especially concerned about.
6. the method for real time discriminating that Aero Engine Testing security parameter as claimed in claim 1 is monitored, it is characterised in that：Institute
The value for stating step (4) is the rated value of security parameter in transient process as obtained by calculating in real time.
7. a kind of real time discriminating system of Aero Engine Testing security parameter monitoring, is based on claim 1 to 5 any one
The method for real time discriminating of described Aero Engine Testing security parameter monitoring, it is characterised in that：The system is pacified including stable state
Population parameter builds table function module, transition state security parameter and builds table function module and in real time monitoring warning function module；
The stable state security parameter builds table function module and is for the key variables that user is especially concerned about, sets up it nominal
The parameter value of limit, the stable state for monitoring warning function in real time differentiates safely；
The transition state security parameter builds the security parameter foundation pass that table function module is for the operation of engine transition state
Bond parameter value, the transition state for monitoring warning function in real time differentiates safely；
The real-time monitoring warning function module be for stable state or transition state are run in process of the test experimental safe monitoring,
Real time discriminating, alarm.
8. the real time discriminating system that Aero Engine Testing security parameter as claimed in claim 7 is monitored, it is characterised in that institute
State stable state security parameter and build the operational process of table function module and be：Table number is given first, is then input into the running status of engine
Parameter, then to uniform section or unit, recently enter all monitored parameter on section and correspondence parameter warning bound and
Failure bound.
9. the real time discriminating system that Aero Engine Testing security parameter as claimed in claim 7 is monitored, it is characterised in that institute
State transition state security parameter and build the operational process of table function module and be：When running first, the operation shape of each key is given
Warning bound and failure bound of the state parameter from a stable state to another stable state, warning bound or failure bound are
One percentage on rated value；In running, if being not reaching to alert bound and failure bound, although or reaching
Confirm to be judged parameter safety to warning bound and failure bound but by button, then by iterative calculation, constantly update
It is judged the rated value of parameter.
10. the real time discriminating system that Aero Engine Testing security parameter as claimed in claim 7 is monitored, it is characterised in that
The operational process of the real-time monitoring warning function module includes the steady-state flow of monitoring in real time and in real time the transition state stream of monitoring
After journey, i.e. program enter monitoring warning function in real time, process selecting is carried out first, judge whether to be monitored in real time into steady state test
Flow, if it is, perform the steady-state flow of monitoring in real time, if it is not, into the transition state flow of real-time monitoring；
The steady-state flow of the real-time monitoring is directly compared by the measured value of stable state security parameter with the rated value in Steady-state Parameters table
Relatively provide judgement；The transition state flow of the real-time monitoring is carried out by the measured value of transition state security parameter with the rated value for calculating
Compare, with realize whether safety differentiation, while calculate rated value by give rule be iterated, eventually form rated value
Tables of data, is matched by tables of data.
The real time discriminating system of 11. Aero Engine Testing security parameter monitoring as claimed in claim 10, it is characterised in that
The update method of the rated value that the stable state security parameter is judged security parameter in differentiating is：New rated value is current nominal
Value and the genic product of current nominal value, add 1 and subtract this genic difference and measure number before current time
According to filter value product.
The real time discriminating system of 12. Aero Engine Testing security parameter monitoring as claimed in claim 10, it is characterised in that
By the update method of the ratings data table of comparison variable in the transition state flow of the real-time monitoring：When by the survey of comparison variable
Must be worth after being judged as normally, update by the two-dimentional ratings data table of comparison variable；The current nominal of reference variable is calculated first
Value, current nominal value is the smothing filtering of the multiple measured values before current measured value；Then, by the current nominal of reference variable
Three pairs of reference variables in value, two-dimentional ratings data table near reference variable current nominal value value with by comparison variable
Data are to calculating by the calculating rated value of comparison variable；Finally, come by calculating rated value, gene, original rated value
The rated value by comparison variable under conditions of with particular reference to variate-value is calculated, table is updated the data.
The real time discriminating system of 13. Aero Engine Testing security parameter monitoring as claimed in claim 10, it is characterised in that
It is by the choosing method of the rated value of comparison variable in the transition state security parameter differentiation：Transition state is by the current of comparison variable
Initial value and stop value of the rated value by reference variable, the initial value and stop value by comparison variable and reference variable work as
Preceding measured value is calculated by linear interpolation and obtained.
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