CN118070153B - Method for diagnosing performance of complete machine test of aero-engine - Google Patents
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Abstract
The application provides a method for diagnosing the performance of an aircraft engine whole machine test, which belongs to the technical field of aircraft engines and comprises the steps of aiming at a plurality of component characteristics of an aircraft engine whole machine system, acquiring a preliminary diagnosis result of the whole machine test performance based on an expansion uncertainty and a system constraint condition corresponding to each component characteristic; and checking and verifying the primary diagnosis result of the whole machine test performance by using the whole machine performance simulation model to obtain the relative deviation between the whole machine performance simulation result and the primary diagnosis result of the whole machine test performance, which are output by the whole machine performance simulation model, until the relative deviation meets the preset precision requirement, and setting the primary diagnosis result of the whole machine test performance as the diagnosis result of the whole machine test performance of the engine. By the processing scheme, the accuracy of the performance diagnosis result of the whole engine test is improved, technical support is provided for accurately diagnosing the performance result and the performance technical state of the whole engine and parts, and a technical foundation is laid for engine performance debugging and fault diagnosis.
Description
Technical Field
The application relates to the technical field of aeroengines, in particular to a method for diagnosing the performance of an aeroengine complete machine test.
Background
The engine complete machine test performance diagnosis technology is an important key technology in the engine development process, can evaluate the performance of each component and the complete machine with high precision according to the gas path parameter measurement value, and has important significance for engine performance judgment, performance debugging, fault diagnosis, health management and the like. At present, the performance evaluation of the whole engine test adopts a process of calculating the cross section, the components and the performance parameters of the whole engine one by one from front to back, the obtained simple evaluation result does not consider the nondeterminacy influence of the characteristic constraint of each system, the precision is low, and the performance results and the performance technical states of the whole engine and the components of the engine cannot be accurately judged. Therefore, the development of the method for diagnosing the performance of the whole test of the aero-engine is a technical problem which must be solved by the performance evaluation of the whole test.
Disclosure of Invention
In view of the above, the embodiment of the application provides a method for diagnosing the performance of the whole test of an aeroengine, which mainly diagnoses the performance of the whole test and the component test by a bench test measurement result and a steady-state performance model, namely, by considering the constraint condition limitation of each system, provides technical support for accurately diagnosing the performance result and the performance technical state of the whole test and the component of the engine, and lays a technical foundation for debugging the performance and fault diagnosis of the engine.
The embodiment of the application provides a method for diagnosing the performance of an aero-engine complete machine test, which comprises the following steps:
Aiming at a plurality of component characteristics of an aircraft engine whole system, acquiring a preliminary diagnosis result of the whole test performance based on the expansion uncertainty and the system constraint conditions corresponding to each component characteristic;
And checking and verifying the primary diagnosis result of the whole machine test performance by using the whole machine performance simulation model to obtain the relative deviation between the whole machine performance simulation result and the primary diagnosis result of the whole machine test performance, which are output by the whole machine performance simulation model, until the relative deviation meets the preset precision requirement, and setting the primary diagnosis result of the whole machine test performance as the diagnosis result of the whole machine test performance of the engine.
According to a specific implementation of an embodiment of the application, the plurality of component characteristics includes a fan component characteristic, a compressor component characteristic, a combustion component characteristic, and a turbine component characteristic.
According to a specific implementation of an embodiment of the present application, the system constraint corresponding to the fan component characteristics includes a constraint that interpolates the result by the fan test characteristics; the system constraint conditions corresponding to the characteristics of the compressor component comprise constraint conditions of interpolation results of the characteristics of the compressor, constraint conditions of interpolation results of the characteristics of the core machine, constraint conditions of iterative calculation results of flow converted through the throat of the high-pressure turbine and constraint conditions of iterative calculation results of total temperature of the outlet of the low-pressure turbine; the system constraint conditions corresponding to the combustion part characteristics include constraint conditions of interpolation results by the combustion characteristics and constraint conditions of calculation results by engineering empirical formulas; the system constraints corresponding to the turbine component characteristics include constraints that interpolate the results from turbine test characteristics.
According to a specific implementation manner of the embodiment of the application, aiming at a plurality of component characteristics of an aircraft engine whole engine system, based on the expansion uncertainty and the system constraint condition corresponding to each component characteristic, a preliminary diagnosis result of the whole engine test performance is obtained, which comprises the following steps:
Aiming at the characteristics of the fan component, the air path parameters are adjusted in the range of the expansion uncertainty to obtain the fan pressure ratio and the fan efficiency, the fan pressure ratio and the fan efficiency meet the interpolation result of the fan test characteristics considering the angle deviation of the fan guide vane, and then the determined fan performance parameters, the fan inlet parameters and the fan outlet parameters are obtained and transmitted backwards;
Aiming at the characteristics of the compressor component, calculating a fan outlet parameter transmitted by a fan and the characteristics of an intermediate casing to obtain a compressor inlet parameter, calculating the converted flow, the pressure ratio and the efficiency of the compressor inlet according to the compressor inlet parameter, the compressor outlet parameter and the characteristics of the compressor component, and adjusting the total temperature and the total pressure of the compressor outlet and the total temperature measurement value of the low-pressure turbine outlet in the range of expanded uncertainty, and simultaneously meeting the system constraint conditions corresponding to the characteristics of the compressor component to obtain the determined compressor performance parameter, the determined compressor inlet parameter and the determined compressor outlet parameter and transmitting the determined compressor outlet parameter backwards;
aiming at the characteristics of the combustion part, the performance parameters of the combustion chamber and the outlet parameters of the combustion chamber are obtained by calculating the outlet parameters of the gas compressor and the fuel flow transmitted by the gas compressor, and the determined performance parameters of the combustion chamber, the inlet parameters of the combustion chamber and the outlet parameters of the combustion chamber are obtained and transmitted backwards by adjusting the input measured value in the range of the expansion uncertainty and simultaneously meeting the system constraint conditions corresponding to the characteristics of the combustion part;
For the characteristics of the turbine component, the power and efficiency transmitted by the fan or the compressor, the combustion chamber outlet parameter transmitted by the combustion chamber and the core machine characteristic are calculated to obtain the high-pressure turbine performance parameter and the high-pressure turbine outlet parameter, and the input measured value is adjusted within the measurement uncertainty range, and the system constraint conditions corresponding to the characteristics of the turbine component are simultaneously met to obtain the determined turbine performance parameter, the turbine inlet parameter and the turbine outlet parameter and then transmitted backwards.
According to a specific implementation manner of the embodiment of the present application, the process of obtaining the extended uncertainty includes:
Performing independent repeated observation on each measured value to obtain each measured value, and performing arithmetic average on each measured value As a measured estimate;
Statistical analysis is carried out on each measured value to obtain standard deviation of measured data of each measured value The calculation formula of the class a standard uncertainty u A of the measured estimation value is:
，
wherein n is the number of measured values, and x is the measured value of the measured parameter;
Class B standard uncertainty u B of the measured estimate is empirically obtained, the measured interval of possible values is [ [ -a，+A ], a is the half width of the measured possible value interval, and the calculation formula of the class B standard uncertainty u B is:
，
Where k 'is a first inclusion factor or confidence factor, k' being determined from the probability distribution and confidence level of the measured measurement;
According to the A-type standard uncertainty U A and the B-type standard uncertainty U B of the measured estimated value, an extended uncertainty U is obtained, and the calculation formula of the extended uncertainty U is as follows:
，
，
where u C is the synthesis standard uncertainty and K is the second inclusion factor.
According to a specific implementation manner of the embodiment of the application, the complete machine performance simulation model is utilized to check and verify the complete machine test performance preliminary diagnosis result, so as to obtain the relative deviation between the complete machine performance simulation result output by the complete machine performance simulation model and the complete machine test performance preliminary diagnosis result until the relative deviation meets the preset precision requirement, and the method comprises the following steps:
according to the design parameters and the characteristics of the components, a complete machine performance simulation model is established;
selecting a component characteristic correction parameter and a target parameter used as a checking reference based on the complete machine performance simulation model;
setting an optimization algorithm according to the component characteristic correction parameters and the target parameters;
And after the setting of the optimization algorithm is completed, performing self-adaptive check on the complete machine performance simulation model, and checking and verifying the complete machine test performance preliminary diagnosis result to obtain the relative deviation between the complete machine performance simulation result output by the complete machine performance simulation model and the complete machine test performance preliminary diagnosis result until the relative deviation meets the preset precision requirement.
According to a specific implementation of the embodiment of the application, the relative deviation is the relative percentage of the target parameter, the relative percentage of the target parameter is the relative percentage of the value of the target parameter in the initial diagnosis result of the whole machine test performance and the whole machine performance simulation result of the corresponding target parameter output by the whole machine performance simulation model,
The preset accuracy requirement is that the arithmetic mean of the relative percentages of all target parameters is less than 0.5% and the relative percentage of a single target parameter is less than 1.0%.
According to a specific implementation of an embodiment of the present application, the component characteristic correction parameters include fan inlet equivalent flow, fan efficiency, compressor inlet equivalent flow, compressor efficiency, high pressure turbine throat equivalent flow, high pressure turbine efficiency, low pressure turbine throat equivalent flow, low pressure turbine efficiency, and mixing chamber outdoor culvert inlet relative area.
According to one specific implementation of an embodiment of the present application, the target parameters include engine thrust, engine fuel consumption, fan inlet converted flow, fan pressure ratio, fan efficiency, compressor inlet converted flow, compressor pressure ratio, compressor efficiency, combustor fuel flow, combustor outlet total temperature, high pressure turbine throat converted flow, high pressure turbine expansion ratio, high pressure turbine efficiency, low pressure turbine throat converted flow, low pressure turbine expansion ratio, low pressure turbine efficiency, and low pressure turbine outlet total temperature.
According to a specific implementation manner of the embodiment of the application, the method further comprises:
And the thrust, the fuel flow and the high-low pressure rotor rotating speed of the engine are used as strong constraint conditions to be input into a complete machine performance simulation model.
The beneficial effects are that:
According to the method for diagnosing the performance of the whole aeroengine test, provided by the embodiment of the application, the nondeterminacy influence factors in the design and test are considered, namely, the nondeterminacy method is firstly introduced, the nondeterminacy influence factors such as the pneumatic design mechanism, the technical state deviation, the test environment difference and the like of all parts are considered based on the whole performance matching technology and the balance principle, and all system constraint limits are provided for the whole test performance diagnosing method, so that the whole test performance result is obtained; and secondly, the performance simulation model and the optimization algorithm of the whole engine are utilized to check and verify the performance results of the whole engine test, so that the accuracy of the performance results of the whole engine and the parts test is improved, technical support is provided for accurately diagnosing the performance results and the performance technical state of the whole engine and the parts, and a technical foundation is laid for the performance debugging and fault diagnosis of the engine.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the main measurement cross section of an aircraft engine complete machine test according to an embodiment of the invention;
FIG. 2 is a flow chart of an aircraft engine complete machine test performance diagnostic method according to an embodiment of the invention;
FIG. 3 is a graph comparing the results of fan inlet converted flow according to an embodiment of the present invention;
FIG. 4 is a graph comparing the results of compressor inlet converted flow according to an embodiment of the present invention;
FIG. 5 is a graph comparing the results of low pressure turbine outlet gas total temperature according to an embodiment of the present invention;
FIG. 6 is a graph comparing the results of low pressure turbine outlet gas total pressure in accordance with an embodiment of the present invention.
In the figure: 2. a fan inlet cross section; 21. inlet section of the compressor; 3. a compressor outlet cross section; 4. a main combustion chamber outlet cross section; 5. a low pressure turbine outlet section; 65. a mixer outlet cross section; 7. a nozzle inlet cross section; 8. nozzle throat section.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present application with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. The application may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present application by way of illustration, and only the components related to the present application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that aspects may be practiced without these specific details.
The embodiment of the application provides a method for diagnosing the overall test performance of an aero-engine, which is described in detail below with reference to fig. 1 to 6.
In one embodiment, a method for diagnosing performance of a complete machine test of an aeroengine is provided, comprising:
Step 1, aiming at a plurality of component characteristics of an aircraft engine whole system, acquiring a preliminary diagnosis result of the whole test performance based on the expansion uncertainty and the system constraint condition corresponding to each component characteristic. Based on the whole machine test performance evaluation method, the step considers measurement uncertainty and constraint conditions of each system to re-evaluate the whole machine test performance as a preliminary diagnosis result of the whole machine test performance. The method is mainly characterized in that the method takes the thrust, the fuel flow and the high-low pressure rotor rotating speed in the actual measurement result of the whole engine test as accurate values to be input, the rest gas path parameters are subjected to uncertainty calculation, the uncertainty of the measurement parameters is obtained, the uncertainty of each measurement parameter is transmitted backwards, and a basis is provided for the preliminary diagnosis of the whole engine test performance.
And 2, checking and verifying the primary diagnosis result of the whole machine test performance by using the whole machine performance simulation model to obtain the relative deviation between the whole machine performance simulation result and the primary diagnosis result of the whole machine test performance, which are output by the whole machine performance simulation model, until the relative deviation meets the preset precision requirement, and setting the primary diagnosis result of the whole machine test performance as the diagnosis result of the whole machine test performance of the engine.
In the whole engine test, the main measurement section is shown in fig. 1, and mainly includes a fan inlet section 2, a compressor inlet section 21, a compressor outlet section 3, a main combustion chamber outlet section 4, a low pressure turbine outlet section 5, a mixer outlet section 65, a nozzle inlet section 7, and a nozzle throat section 8.
Specifically, the plurality of component characteristics includes a fan component characteristic, a compressor component characteristic, a combustion component characteristic, and a turbine component characteristic. The system constraints corresponding to the fan component characteristics include constraints that interpolate the results by fan test characteristics; the system constraint conditions corresponding to the characteristics of the compressor component comprise constraint conditions of interpolation results of the characteristics of the compressor, constraint conditions of interpolation results of the characteristics of the core machine, constraint conditions of iterative calculation results of flow converted through the throat of the high-pressure turbine and constraint conditions of iterative calculation results of total temperature of the outlet of the low-pressure turbine; the system constraint conditions corresponding to the combustion part characteristics include constraint conditions of interpolation results by the combustion characteristics and constraint conditions of calculation results by engineering empirical formulas; the system constraints corresponding to the turbine component characteristics include constraints that interpolate the results from turbine test characteristics.
More specifically, the following details are given for step 1:
1) Introducing a measurement uncertainty theory and method, carrying out measurement error analysis on the measurement parameters of the whole machine rack test, obtaining a containing interval of the measurement parameters, and providing measurement system constraint for the whole machine test performance diagnosis method, namely considering constraint in the containing interval on the basis of a measurement result;
2) The fan component characteristics provide fan characteristic constraint for the whole machine test performance diagnosis method, and performance parameters such as flow, pressure ratio, efficiency and the like of the fan inlet are limited mainly through two dimensions, firstly, constraint of a containing interval is considered, secondly, constraint of a fan test characteristic interpolation result is adopted, and initial values of the fan performance parameters are preliminarily locked through the two dimensions;
3) The characteristics of the components of the air compressor provide the characteristic constraint of the air compressor for the whole machine test performance diagnosis method, the performance parameters such as the conversion flow of an inlet of the air compressor, the pressure ratio, the efficiency and the like are limited mainly through five dimensions, the constraint of the included interval is considered, the constraint of the interpolation result of the characteristics of the air compressor is considered, the constraint of the interpolation result of the characteristics of the core machine is considered, the constraint of the iteration calculation result of the conversion flow of a throat part of the high-pressure turbine is considered, the constraint of the iteration calculation result of the total temperature of an outlet of the low-pressure turbine is considered, and the initial value of the performance parameters of the air compressor is preliminarily locked through the five dimensions;
4) The combustion part characteristics provide combustion characteristic constraint for the whole machine test performance diagnosis method, performance parameters such as combustion efficiency, total pressure recovery and the like are limited mainly through three dimensions, namely, constraint of a contained interval is considered, constraint of a combustion characteristic interpolation result is considered, constraint of a result is calculated through an engineering empirical formula, and initial values of the combustion performance parameters are preliminarily locked through the three dimensions;
5) The turbine component characteristics provide turbine characteristic constraint for the whole machine test performance diagnosis method, the turbine throat conversion flow, expansion ratio and the like are mainly limited through two dimensions, firstly, the constraint of a containing section is considered, secondly, the constraint of a turbine test characteristic interpolation result is adopted, and the initial value of turbine performance parameters is preliminarily locked through the two dimensions;
6) The strong constraint characteristic provides strong constraint limitation for the whole machine test performance diagnosis method, the accuracy of the measurement results is high according to the measurement principle of the thrust, the fuel flow and the high-low pressure rotor rotating speed and engineering experience, the thrust, the fuel flow and the high-low pressure rotor rotating speed can be defined as strong constraint conditions, and the measurement results of the thrust, the fuel flow and the high-low pressure rotor rotating speed are considered to be accurate values.
The simulation verification step for the complete machine performance model in the step 2 can be detailed as follows:
1) According to the design point parameters and the component characteristics (universal characteristics can be selected) of the whole machine, a performance simulation model of the whole machine is established;
2) On the basis of the performance simulation model of the whole machine, integrating an optimization algorithm of multi-parameter correction and multi-target constraint restriction;
3) Selecting correction parameters of the characteristics of each system and setting upper and lower limits of correction amounts, wherein the correction parameters are mainly used for correcting the characteristics of each system;
4) Selecting target parameters and setting the target parameters as checking references, wherein the target parameters are mainly main performance parameters of the whole machine;
5) After the setting of the optimization algorithm is completed, the self-adaption checking of the performance simulation model of the whole machine is started, and the initial diagnosis result of the test performance of the whole machine is checked and verified;
6) Checking result judgment, wherein if the arithmetic average value of the relative percentages of the target parameters is smaller than 0.5% and the relative percentage of the single target parameter is smaller than 1.0%, the whole machine test performance evaluation result is considered to meet the pneumatic balance condition of the engine, and the whole machine test performance preliminary diagnosis result is the whole machine test performance diagnosis result; otherwise, the evaluation result of the test performance of the whole machine is considered to not meet the pneumatic balance condition of the engine or the diagnosis precision is low, and the test performance diagnosis of the whole machine is required to be carried out again according to the preliminary diagnosis step of the test performance of the whole machine.
In one embodiment, the process of acquiring the extended uncertainty is described in detail, and specifically includes:
Step 111, independently and repeatedly observing each measured value to obtain each measured value, and averaging the arithmetic mean value of each measured value As a measured estimate;
step 112, performing statistical analysis on each measured value to obtain each measured data standard deviation The calculation formula of the class a standard uncertainty u A of the measured estimation value is:
，
wherein n is the number of measured values, and x is the measured value of the measured parameter;
Step 113, the class B standard uncertainty u B of the measured estimate is obtained empirically, the measured range of possible values is [ [ -a，+A ], a is the half width of the measured possible value interval, and the calculation formula of the class B standard uncertainty u B is:
，
Where k 'is a first inclusion factor or confidence factor, assuming that the measured value is a probability distribution, k' is determined from the probability distribution of the measured value and the confidence level p;
Step 114, obtaining an expanded uncertainty U according to the class A standard uncertainty U A and the class B standard uncertainty U B of the measured estimated value, wherein the calculation formula of the expanded uncertainty U is as follows:
，
，
where u C is the synthesis standard uncertainty and K is the second inclusion factor.
The extended uncertainty U is obtained by multiplying the synthesis standard uncertainty by a second inclusion factor, typically a second inclusion factor of 2 or 3, and in most cases a constraint of 2, where the distribution of measured Y is close to normal, the interval inclusion probability for k=2 is about 95% and the interval inclusion probability for k=3 is about 99%.
In one embodiment, for a plurality of component characteristics of an aircraft engine overall system, obtaining an overall test performance preliminary diagnostic result based on an expansion uncertainty and a system constraint condition corresponding to each component characteristic, includes:
Step 121, aiming at the characteristics of the fan component, the air path parameters are adjusted within the range of the expansion uncertainty to obtain the fan pressure ratio and the fan efficiency, the fan pressure ratio and the fan efficiency are enabled to meet the interpolation result of the fan test characteristics considering the angle deviation of the fan guide vane, and then the determined fan performance parameters, the fan inlet parameters and the fan outlet parameters are obtained and transmitted backwards.
Specifically, the fan flow is calculated according to the total static pressure and total temperature measured by the flow tube, the fan pressure ratio and efficiency are calculated by combining the total temperature and total pressure measured value of the fan outlet, the fan pressure ratio and efficiency are calculated by adjusting the air path parameters in the containing interval, so that the fan pressure ratio and efficiency meet the constraint limit of the fan test characteristics, and the determined fan performance parameters, the fan inlet parameters and the fan outlet parameters are transmitted backwards.
Gas velocity coefficient：
，
Wherein: measuring total pressure for the flow tube in kPa; measuring static pressure for the flow tube, unit kPa; the specific heat ratio of air is 1.4;
function of gas flow ：
，
Fan inlet physical flow：
，
Wherein: c is the flow rate to calculate the gas coefficient,; R is a gas constant, unit J/(kg.K); p t1 is the total pressure measured by the flow tube, and the unit is kPa; Measuring the total temperature of the flow tube in K; The cross-sectional area is measured for the flow tube in m 2; The flow coefficient of the flow pipe is searched by a blowing test curve of the flow pipe;
Flow conversion for fan inlet ：
，
Wherein: The total temperature of the inlet of the fan is shown as a unit K; The total pressure of the inlet of the fan is unit kPa;
Relative conversion rotational speed of fan ：
，
Wherein: fan relative physical rotational speed, unit;
Fan boost ratio ：
，
Wherein: The total pressure of the outlet of the fan is unit kPa;
Isentropic efficiency of fan ：
，
Wherein: The total temperature of the fan outlet is in unit K; The total heat insulation temperature of the outlet of the fan is given by a unit K; The specific heat is fixed for the inlet pressure of the fan, Constant pressure specific heat for the fan outlet; Adiabatic constant pressure specific heat for the fan outlet.
Fan inlet converted flow calculated by fan test characteristic interpolation considering fan guide vane angle deviation：
，
Wherein: f 1 is a fan inlet conversion flow calculation function; w af,c </SUB > is a fan inlet converted flow array, the unit kg/s, pi f </SUB > is a fan boost ratio array,Fan guide vane angles corresponding to the whole machine test are in unit degrees; fan vane angles corresponding to fan component tests are measured in degrees; converting a flow correction coefficient for a fan inlet corresponding to the fan guide vane angle of 1 DEG;
Fan power The method comprises the following steps:
。
Step 122, calculating a compressor inlet parameter according to the fan outlet parameter transmitted by the fan and the intermediate casing characteristic aiming at the compressor component characteristic, calculating a compressor inlet conversion flow, a pressure ratio and efficiency according to the compressor inlet parameter, the compressor outlet parameter and the compressor component characteristic, adjusting the total temperature and total pressure of the compressor outlet and the total temperature and measured value of the low-pressure turbine outlet within the range of expansion uncertainty, and simultaneously meeting the system constraint condition corresponding to the compressor component characteristic, thereby obtaining the determined compressor performance parameter, the determined compressor inlet parameter, the determined compressor outlet parameter and the determined backward transmission.
Specifically, the fan outlet parameter and the intermediate casing characteristic transmitted by the fan are calculated to obtain the air compressor inlet parameter, the air compressor inlet conversion flow, the pressure ratio, the efficiency and the like are calculated according to the air compressor inlet parameter, the air compressor outlet parameter and the component characteristic, the measurement uncertainty, the air compressor characteristic, the core machine characteristic, the high-pressure turbine throat conversion flow characteristic and the constraint limit of the low-pressure turbine outlet total temperature are simultaneously met after the air compressor outlet total temperature total pressure and the low-pressure turbine outlet total temperature measured value are adjusted within the measurement uncertainty range, and the determined air compressor performance parameter, the air compressor inlet parameter and the air compressor outlet parameter are transmitted backwards.
Total inlet temperature of air compressor：
；
Total pressure of inlet of air compressor：
，
Wherein: Is the total pressure recovery coefficient of the intermediate casing;
Relative conversion rotational speed of air compressor ：
，
Wherein: The relative physical rotation speed of the compressor is given in units; The total inlet temperature of the point compressor is designed as a unit K;
Conversion rotating speed of compressor relative to engine inlet ：
；
Compressor boost ratio：
，
Wherein: is the total pressure of the outlet of the air compressor, and is unit kPa;
isentropic efficiency of compressor ：
，
Wherein: The total temperature of the outlet of the air compressor is shown as a unit K; the total heat insulation temperature of the outlet of the air compressor is given by a unit K; The specific heat is fixed for the inlet pressure of the compressor, The specific heat is fixed for the outlet of the compressor; Adiabatic constant pressure specific heat for the outlet of the compressor;
calculating the converted flow of the inlet of the compressor through the interpolation of the test characteristics of the compressor ：
，
Wherein: f 2 is a first compressor inlet converted flow calculation function; w aC,c </SUB > is an array of converted flow rates at the inlet of the compressor, the unit kg/s, pi C </SUB > is an array of supercharging ratios of the compressor,The corresponding compressor guide vane angle of the whole machine test is in unit degree; the corresponding compressor guide vane angle is tested for the compressor component, and the unit degree is shown in the specification; Converting a flow correction coefficient for a compressor inlet corresponding to the angle of the compressor guide vane of 1 DEG;
calculating the converted flow of the inlet of the compressor through the test characteristic interpolation of the core machine ：
，
Wherein: f 3 is a flow calculation function converted by the inlet of the second compressor; [] The unit is the relative conversion rotating speed array of the air compressor; The angle of the corresponding compressor guide vane is tested for the core machine, and the unit degree is shown; Converting a flow correction coefficient for a compressor inlet corresponding to the angle of the compressor guide vane of 1 DEG;
Iterative calculation of compressor inlet converted flow through high-pressure turbine throat converted flow ：
，
Wherein: f 4 is a flow calculation function converted by the inlet of the third compressor; the fuel flow rate of the combustion chamber is in kg/s; the flow is converted for the throat part of the high-pressure turbine, and the unit is kg/s;
iterative calculation of compressor inlet converted flow through low-pressure turbine outlet total temperature ：
，
Wherein: f 5 is a fourth compressor inlet converted flow calculation function; The unit K is a low-pressure turbine outlet total temperature measurement value;
Air flow rate at inlet of compressor:
；
engine bypass ratio B:
；
Power of air compressor The method comprises the following steps:
，
Wherein: the zero-level air-entraining amount of the air compressor is in kg/s; the unit kg/s is the middle stage bleed air amount of the air compressor; The specific heat is fixed for the middle stage of the compressor; The total temperature of the middle stage of the air compressor is in unit K.
Step 123, aiming at the characteristics of the combustion part, calculating the performance parameters of the combustion chamber and the outlet parameters of the combustion chamber by the outlet parameters of the gas compressor and the fuel flow transmitted by the gas compressor, and obtaining the determined performance parameters of the combustion chamber, the inlet parameters of the combustion chamber and the outlet parameters of the combustion chamber by adjusting the input measured values in the range of the expansion uncertainty and simultaneously meeting the corresponding system constraint conditions of the characteristics of the combustion part (simultaneously meeting the constraint limits of the measurement uncertainty and the combustion characteristics).
Combustor inlet air flow：
，
Wherein: The unit kg/s is the bleed air amount at the outlet of the air compressor;
combustion chamber outlet gas flow ：
；
Wherein: w fb is the fuel flow of the combustion chamber, and the unit is kg/s.
Mach number of combustor inlet：
；
Wherein: f 6 is a combustion chamber inlet doherty calculation function;
residual gas coefficient of combustion chamber ：
；
Combustion chamber oil gas ratio：
；
Combustion efficiency of combustion chamber：
；
Wherein: f 7 is a combustion efficiency calculation function of the combustion chamber;
total pressure recovery coefficient of combustion chamber ：
；
Wherein: f 8 is a function for calculating the total pressure recovery coefficient of the combustion chamber;
Unit enthalpy value of combustion chamber outlet ：
，
Wherein: the unit enthalpy value is the unit kJ/kg of the outlet of the compressor; the unit is kJ/kg which is the low calorific value of fuel;
total temperature of combustion chamber outlet ：
；
Wherein: f 9 is a total temperature calculation function of the outlet of the combustion chamber;
Total pressure of combustion chamber outlet ：
。
Step 124, calculating the high-pressure turbine performance parameter and the high-pressure turbine outlet parameter according to the power and efficiency transmitted by the fan or the compressor, the combustion chamber outlet parameter transmitted by the combustion chamber and the core engine characteristic, and obtaining the determined turbine performance parameter, turbine inlet parameter and turbine outlet parameter and transmitting the determined turbine performance parameter, turbine inlet parameter and turbine outlet parameter backwards by adjusting the input measured value in the measurement uncertainty range and simultaneously meeting the system constraint condition corresponding to the turbine component characteristic.
Throat flow of high pressure turbine：
，
Wherein: introducing cool air quantity before the throat part of the high-pressure turbine to the outlet of the gas compressor, wherein the cool air quantity is in kg/s;
High pressure turbine throat gas-oil ratio ：
；
High pressure turbine throat unit enthalpy value：
；
High pressure turbine throat total temperature：
；
Wherein: f 10 is a high-pressure turbine throat total temperature calculation function;
Throat specific heat ratio of high-pressure turbine ：
；
Wherein: f 11 is a high-pressure turbine throat specific heat ratio calculation function;
High pressure turbine throat total pressure ：
；
High pressure turbine throat converted flow：
；
Obtaining the core machine pressure ratio by interpolation calculation of the core machine characteristics：
；
Wherein: f 12 is a core mechanical pressure ratio calculation function;
High pressure turbine outlet total pressure ：
；
High pressure turbine expansion ratio：
；
High pressure turbine actual power：
，
Wherein: The unit kW is accessory power; mechanical efficiency is high-pressure shaft;
high pressure turbine efficiency ：
；
Low pressure turbine throat flow：
，
Wherein: introducing the cold air quantity before the throat part of the low-pressure turbine into the middle of the air compressor, wherein the unit is kg/s;
low pressure turbine throat oil gas ratio ：
；
Low pressure turbine throat unit enthalpy value：
；
Wherein: The unit enthalpy value of the middle bleed air of the air compressor is unit kJ/kg;
Low pressure turbine throat total temperature ：
；
Wherein: f 13 is a low-pressure turbine throat total temperature calculation function;
low pressure turbine throat specific heat ratio ：
；
Wherein: f 14 is a low pressure turbine throat specific heat ratio calculation function;
Low pressure turbine expansion ratio ：
，
Wherein: is a low pressure turbine outlet total pressure measurement, unit kPa;
Low pressure turbine actual power ：
，
Wherein: Mechanical efficiency for low pressure shaft;
Low pressure turbine efficiency ：
；
Low pressure turbine outlet flow：
；
Low pressure turbine outlet gas-oil ratio：
；
Low pressure turbine outlet unit enthalpy value：
；
Low pressure turbine outlet total temperature calculation：
。
Wherein: and f 15 is a calculation function of the total temperature of the outlet of the low-pressure turbine.
The constraint limit of each system is completed through the steps, the measurement correction value of the air path parameters and the performance result of the components of the whole engine test taking the constraint of each system into consideration are preliminarily determined, and the preliminary diagnosis result of the whole engine test performance is obtained according to the evaluation flow of the whole engine test performance in the right box in fig. 2, wherein the sign meaning in the figure is as follows: d is the diameter of an inlet of the engine, and the unit is m; n F is the physical rotation speed of the fan, and the unit is r/min; n F,dp is the physical rotating speed of the fan at the design point, and the unit is r/min; n C is the physical rotation speed of the compressor, and the unit is r/min; n C,dp is the physical rotating speed of the design point air compressor, and the unit is r/min; t t5 is the total temperature of the outlet of the low-pressure turbine, and the unit is K; p t16 is total pressure of an external culvert outlet, and the unit is kPa; t t16 is total temperature of an external culvert outlet, and the unit is K; w fab is afterburner fuel flow, unit kg/s; Is afterburner combustion efficiency.
And secondly, executing a complete machine performance model simulation verification step, namely checking and verifying the initial diagnosis result of the complete machine test performance by the complete machine performance simulation model.
In one embodiment, the method for checking and verifying the primary diagnosis result of the overall test performance by using the overall performance simulation model to obtain the relative deviation between the overall performance simulation result output by the overall performance simulation model and the primary diagnosis result of the overall test performance until the relative deviation meets the preset precision requirement comprises the following steps:
Step 201, a complete machine performance simulation model is established according to complete machine design parameters and component characteristics. Considering that the model mainly plays a role in checking and verifying the accuracy of the initial diagnosis result of the test performance of the whole machine, the component characteristic selection is a selectable general characteristic;
Step 202, selecting a component characteristic correction parameter and a target parameter used as a checking reference based on the whole machine performance simulation model. Setting upper and lower limits of correction quantity of component characteristic correction parameters, wherein the upper and lower limits of correction quantity are usually determined according to the difference between component selection characteristics and component real characteristics;
Step 203, setting an optimization algorithm according to the component characteristic correction parameters and the target parameters. On the basis of the established complete machine performance simulation model, integrating optimization algorithms of multi-parameter correction and multi-target parameter constraint restriction, wherein a particle swarm differential evolution optimization algorithm is generally selected;
And 204, performing self-adaptive checking of the complete machine performance simulation model after the optimization algorithm is set, checking and verifying the complete machine test performance preliminary diagnosis result to obtain the relative deviation of the complete machine performance simulation result output by the complete machine performance simulation model and the complete machine test performance preliminary diagnosis result until the relative deviation meets the preset precision requirement, wherein the complete machine test performance preliminary diagnosis result is the complete machine test performance diagnosis result, and if the preset precision requirement cannot be met, performing complete machine test performance diagnosis again according to the complete machine test performance preliminary diagnosis step.
Specifically, the relative deviation is the relative percentage of the target parameter, the relative percentage of the target parameter is the relative percentage of the value of the target parameter in the initial diagnosis result of the whole machine test performance and the whole machine performance simulation result of the corresponding target parameter output by the whole machine performance simulation model,
The preset accuracy requirement is that the arithmetic mean of the relative percentages of all target parameters is less than 0.5% and the relative percentage of a single target parameter is less than 1.0%.
In one embodiment, the component characteristic correction parameters include fan inlet equivalent flow, fan efficiency, compressor inlet equivalent flow, compressor efficiency, high pressure turbine throat equivalent flow, high pressure turbine efficiency, low pressure turbine throat equivalent flow, low pressure turbine efficiency, and mixing chamber external culvert inlet relative area.
In one embodiment, the target parameters include engine thrust, engine fuel consumption, fan inlet converted flow, fan pressure ratio, fan efficiency, compressor inlet converted flow, compressor pressure ratio, compressor efficiency, combustor fuel flow, combustor outlet total temperature, high pressure turbine throat converted flow, high pressure turbine expansion ratio, high pressure turbine efficiency, low pressure turbine throat converted flow, low pressure turbine expansion ratio, low pressure turbine efficiency, and low pressure turbine outlet total temperature.
In one embodiment, the method further comprises:
And the thrust, the fuel flow and the high-low pressure rotor rotating speed of the engine are used as strong constraint conditions to be input into a complete machine performance simulation model.
According to the method for diagnosing the performance of the whole test of the aero-engine in the embodiment, the diagnosis results are shown in fig. 3 to 6, and the ordinate in the figures is the absolute deviation of the analysis-diagnosis-simulation result relative to the mean value of the three results. The results show that: the method for diagnosing the performance of the whole test of the aeroengine, provided by the application, carries out cross coupling analysis on the design and test results, mutually checks and verifies, and the diagnosis results are a group of reasonable and feasible performance results in the inclusion interval of the real results, so that the accuracy of the performance diagnosis results of the whole test is improved.
According to the embodiment provided by the invention, the nondeterminacy influence factors in the design and test are considered, namely, an uncertainty method is introduced firstly, the nondeterminacy influence factors such as pneumatic design mechanisms, technical state deviation, test environment difference and the like of all parts are considered based on a complete machine performance matching technology and a balance principle, all system constraint limits are provided for a complete machine test performance diagnosis method, and a complete machine test performance result is obtained; and secondly, the performance simulation model and the optimization algorithm of the whole engine are utilized to check and verify the performance results of the whole engine test, so that the accuracy of the performance results of the whole engine and the parts test is improved, technical support is provided for accurately diagnosing the performance results and the performance technical state of the whole engine and the parts, and a technical foundation is laid for the performance debugging and fault diagnosis of the engine.
The present application is not limited to the above embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present application are intended to be included in the scope of the present application. Therefore, the protection scope of the application is subject to the protection scope of the claims.
Claims (7)
1. The method for diagnosing the performance of the complete machine test of the aero-engine is characterized by comprising the following steps of:
Aiming at a plurality of component characteristics of an aircraft engine whole system, acquiring a preliminary diagnosis result of the whole test performance based on the expansion uncertainty and the system constraint conditions corresponding to each component characteristic;
Checking and verifying the primary diagnosis result of the whole machine test performance by using the whole machine performance simulation model to obtain the relative deviation between the whole machine performance simulation result and the primary diagnosis result of the whole machine test performance output by the whole machine performance simulation model until the relative deviation meets the preset precision requirement, and setting the primary diagnosis result of the whole machine test performance as the diagnosis result of the whole machine test performance of the engine;
wherein the plurality of component characteristics includes a fan component characteristic, a compressor component characteristic, a combustion component characteristic, and a turbine component characteristic; the system constraints corresponding to the fan component characteristics include constraints that interpolate the results by fan test characteristics; the system constraint conditions corresponding to the characteristics of the compressor component comprise constraint conditions of interpolation results of the characteristics of the compressor, constraint conditions of interpolation results of the characteristics of the core machine, constraint conditions of iterative calculation results of flow converted through the throat of the high-pressure turbine and constraint conditions of iterative calculation results of total temperature of the outlet of the low-pressure turbine; the system constraint conditions corresponding to the combustion part characteristics include constraint conditions of interpolation results by the combustion characteristics and constraint conditions of calculation results by engineering empirical formulas; the system constraints corresponding to the turbine component characteristics include constraints that interpolate results from turbine test characteristics;
The method for obtaining the initial diagnosis results of the test performance of the whole aircraft engine based on the expansion uncertainty and the system constraint conditions corresponding to each component characteristic aiming at the characteristics of a plurality of components of the whole aircraft engine comprises the following steps:
Aiming at the characteristics of the fan component, the air path parameters are adjusted in the range of the expansion uncertainty to obtain the fan pressure ratio and the fan efficiency, the fan pressure ratio and the fan efficiency meet the interpolation result of the fan test characteristics considering the angle deviation of the fan guide vane, and then the determined fan performance parameters, the fan inlet parameters and the fan outlet parameters are obtained and transmitted backwards;
Aiming at the characteristics of the compressor component, calculating a fan outlet parameter transmitted by a fan and the characteristics of an intermediate casing to obtain a compressor inlet parameter, calculating the converted flow, the pressure ratio and the efficiency of the compressor inlet according to the compressor inlet parameter, the compressor outlet parameter and the characteristics of the compressor component, and adjusting the total temperature and the total pressure of the compressor outlet and the total temperature measurement value of the low-pressure turbine outlet in the range of expanded uncertainty, and simultaneously meeting the system constraint conditions corresponding to the characteristics of the compressor component to obtain the determined compressor performance parameter, the determined compressor inlet parameter and the determined compressor outlet parameter and transmitting the determined compressor outlet parameter backwards;
aiming at the characteristics of the combustion part, the performance parameters of the combustion chamber and the outlet parameters of the combustion chamber are obtained by calculating the outlet parameters of the gas compressor and the fuel flow transmitted by the gas compressor, and the determined performance parameters of the combustion chamber, the inlet parameters of the combustion chamber and the outlet parameters of the combustion chamber are obtained and transmitted backwards by adjusting the input measured value in the range of the expansion uncertainty and simultaneously meeting the system constraint conditions corresponding to the characteristics of the combustion part;
For the characteristics of the turbine component, the power and efficiency transmitted by the fan or the compressor, the combustion chamber outlet parameter transmitted by the combustion chamber and the core machine characteristic are calculated to obtain the high-pressure turbine performance parameter and the high-pressure turbine outlet parameter, and the input measured value is adjusted within the measurement uncertainty range, and the system constraint conditions corresponding to the characteristics of the turbine component are simultaneously met to obtain the determined turbine performance parameter, the turbine inlet parameter and the turbine outlet parameter and then transmitted backwards.
2. The method for diagnosing complete machine test performance of an aircraft engine according to claim 1, wherein the process of obtaining the expansion uncertainty comprises:
Performing independent repeated observation on each measured value to obtain each measured value, and performing arithmetic average on each measured value As a measured estimate;
Statistical analysis is carried out on each measured value to obtain standard deviation of measured data of each measured value The calculation formula of the class a standard uncertainty u A of the measured estimation value is:
，
wherein n is the number of measured values, and x is the measured value of the measured parameter;
Class B standard uncertainty u B of the measured estimate is empirically obtained, the measured interval of possible values is [ [ -a，+A ], a is the half width of the measured possible value interval, and the calculation formula of the class B standard uncertainty u B is:
，
Where k 'is a first inclusion factor or confidence factor, k' being determined from the probability distribution and confidence level of the measured measurement;
According to the A-type standard uncertainty U A and the B-type standard uncertainty U B of the measured estimated value, an extended uncertainty U is obtained, and the calculation formula of the extended uncertainty U is as follows:
，
，
where u C is the synthesis standard uncertainty and K is the second inclusion factor.
3. The method for diagnosing performance of a complete machine test of an aircraft engine according to claim 1, wherein the step of checking and verifying the complete machine test performance preliminary diagnosis result by using a complete machine performance simulation model to obtain a relative deviation between the complete machine performance simulation result output by the complete machine performance simulation model and the complete machine test performance preliminary diagnosis result until the relative deviation meets a preset accuracy requirement, comprises:
according to the design parameters and the characteristics of the components, a complete machine performance simulation model is established;
selecting a component characteristic correction parameter and a target parameter used as a checking reference based on the complete machine performance simulation model;
setting an optimization algorithm according to the component characteristic correction parameters and the target parameters;
And after the setting of the optimization algorithm is completed, performing self-adaptive check on the complete machine performance simulation model, and checking and verifying the complete machine test performance preliminary diagnosis result to obtain the relative deviation between the complete machine performance simulation result output by the complete machine performance simulation model and the complete machine test performance preliminary diagnosis result until the relative deviation meets the preset precision requirement.
4. The method for diagnosing performance of a complete machine test of an aircraft engine according to claim 3, wherein the relative deviation is a relative percentage of a target parameter, the relative percentage of the target parameter is a relative percentage of a value of the target parameter in the preliminary diagnosis result of performance of the complete machine test and a simulation result of performance of the complete machine corresponding to the target parameter output by the simulation model of performance of the complete machine,
The preset accuracy requirement is that the arithmetic mean of the relative percentages of all target parameters is less than 0.5% and the relative percentage of a single target parameter is less than 1.0%.
5. The method for diagnosing complete machine test performance of an aircraft engine as recited in claim 3, wherein the component characteristic correction parameters include fan inlet equivalent flow, fan efficiency, compressor inlet equivalent flow, compressor efficiency, high pressure turbine throat equivalent flow, high pressure turbine efficiency, low pressure turbine throat equivalent flow, low pressure turbine efficiency, and mixing chamber culvert inlet relative area.
6. The method for diagnosing complete machine test performance of an aircraft engine as recited in claim 3, wherein the target parameters include engine thrust, engine fuel consumption, fan inlet converted flow, fan pressure ratio, fan efficiency, compressor inlet converted flow, compressor pressure ratio, compressor efficiency, combustor fuel flow, combustor outlet total temperature, high pressure turbine throat converted flow, high pressure turbine expansion ratio, high pressure turbine efficiency, low pressure turbine throat converted flow, low pressure turbine expansion ratio, low pressure turbine efficiency, and low pressure turbine outlet total temperature.
7. The aircraft engine complete machine test performance diagnostic method of claim 1, further comprising:
And the thrust, the fuel flow and the high-low pressure rotor rotating speed of the engine are used as strong constraint conditions to be input into a complete machine performance simulation model.
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