CN113899557B - Method and device for determining characteristics of an aeroengine air system - Google Patents
Method and device for determining characteristics of an aeroengine air system Download PDFInfo
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Abstract
The disclosure provides a method and a device for determining characteristics of an air system of an aero-engine, and relates to the field of aero-engines. Based on the characteristic test data of the air system in the low-rotation-speed stage of the aero-engine, constructing a prediction model of the air system characteristic representing the characteristic change rule of the air system; and predicting the characteristic data of the air system at the high rotating speed stage of the aero-engine by using the prediction model. And (3) finding out a characteristic change rule of the air system by utilizing characteristic test data of the air system in a low-rotation-speed stage of the aero-engine, constructing a corresponding prediction model, and obtaining the characteristic data of the air system in a high-rotation-speed stage of the aero-engine through prediction.
Description
Technical Field
The present disclosure relates to the field of aircraft engines, and more particularly to a method and apparatus for determining characteristics of an aircraft engine air system.
Background
In production practice, it is important to obtain characteristic data of the air system of an aeroengine, which can be used to guide the design of the aeroengine, evaluate the characteristics of the aeroengine, etc.
The characteristic data of the air system of the low-rotation stage of the aeroengine can be obtained through testing. The inventors have found that it is also necessary to know in advance the characteristic data of the air system at the high rotational speed stage of the aircraft engine in order to determine the safety of the aircraft engine at the fixed high rotational speed, etc.
Disclosure of Invention
According to the embodiment of the disclosure, the characteristic test data of the air system in the low-rotation-speed stage of the aero-engine are utilized to find out the characteristic change rule of the air system, a corresponding prediction model is constructed, and the characteristic data of the air system in the high-rotation-speed stage of the aero-engine is obtained through prediction.
Some embodiments of the present disclosure provide a method of determining an air system characteristic of an aircraft engine, comprising:
based on the characteristic test data of the air system in the low-rotation-speed stage of the aero-engine, constructing a prediction model of the air system characteristic representing the characteristic change rule of the air system;
and predicting the characteristic data of the air system at the high rotating speed stage of the aero-engine by using the prediction model.
In some embodiments, the aeroengine low speed phase includes a baseline local history including: a low rotational speed rising stage of the aero-engine and a low rotational speed stabilizing stage of the aero-engine; constructing the prediction model, including:
according to the test data of the temperature of the air system and the outlet temperature of the high-pressure compressor in the low-rotation-speed rising stage of the aero-engine, a first prediction model taking the outlet temperature of the high-pressure compressor as an independent variable and taking the temperature of the air system as an independent variable is constructed;
according to the test data of the temperature rise of the air system in unit time of the low-rotation-speed stable stage of the aero-engine, constructing a second prediction model taking time as an independent variable and taking the temperature rise of the air system in unit time as a dependent variable;
and taking the first prediction model and the second prediction model as prediction models for predicting the temperature of the air system.
In some embodiments, the first predictive model is a linear relationship model; the second predictive model is a logarithmic relationship model.
In some embodiments, predicting performance data of an air system of an aircraft engine during a high speed phase includes:
obtaining a set prediction target and a test history of an aero-engine high-speed stage, wherein the aero-engine high-speed stage comprises at least one local history to be predicted, the prediction target comprises a target speed of the aero-engine and a target stable time on the target speed, the test history comprises a reference local history 0 and at least one local history to be predicted, and the characteristic test data also comprises a temperature change delta T0 of an air system in a low-speed stable stage of the aero-engine;
determining the temperature Tn of the air system corresponding to the target rotating speed according to the first prediction model and the outlet temperature of the high-pressure compressor corresponding to the target rotating speed;
according to the second prediction model, combining a test course and a target stabilization time, determining a temperature change delta Ti of an air system in a high-speed stable stage of the aeroengine in each local course i to be predicted and a temperature change delta Tn' of the air system in a target stabilization time in a high-speed stable stage of the aeroengine in a local course n to be predicted in which the target speed is positioned, wherein the local course i to be predicted is a local course to be predicted between a reference local course 0 and the local course n to be predicted in which the target speed is positioned;
and determining the corresponding predicted temperature of the air system at the predicted target according to Tn, deltaT 0, deltaTi and deltaTn'.
In some embodiments, determining Δti and Δtn' includes:
according to the test process, respectively inputting the duration time of the high-rotation-speed stable stage of the aeroengine in each local process i to be predicted into the second prediction model, and respectively outputting each DeltaTi;
and inputting the target stable time on the target rotating speed into the second prediction model according to the test process, and outputting delta Tn'.
In some embodiments, the accumulated values of Tn, ΔT0, ΔTi, and ΔTn' are determined as the corresponding predicted temperatures of the air system at the predicted targets.
In some embodiments, n ranges from 1 to 3.
In some embodiments, the aeroengine low speed phase includes a baseline local history; constructing the prediction model, including: and constructing a third prediction model which takes the outlet pressure of the high-pressure compressor as an independent variable and the pressure of the air system as a dependent variable according to test data of the pressure of the air system and the outlet pressure of the high-pressure compressor in the reference local process, and taking the third prediction model as a prediction model for predicting the pressure of the air system.
In some embodiments, the third predictive model is a linear relationship model.
In some embodiments, predicting performance data of an air system of an aircraft engine during a high speed phase includes:
acquiring a predicted target of a set high-speed stage of the aero-engine, wherein the predicted target comprises a target speed of the aero-engine;
and determining the pressure of the air system corresponding to the target rotating speed according to the third prediction model and the outlet pressure of the high-pressure compressor corresponding to the target rotating speed.
In some embodiments, the characteristic test data is characteristic test data of a chamber of the air system; the predictive model is a predictive model of a characteristic of the chamber of the air system; the predicted characteristic data is characteristic data of the chamber of the air system of the high rotational speed phase of the aircraft engine.
Some embodiments of the present disclosure provide an apparatus for determining characteristics of an aircraft engine air system, comprising: a memory; and a processor coupled to the memory, the processor configured to perform the method of determining an aeroengine air system characteristic of any of the embodiments based on instructions stored in the memory.
Some embodiments of the present disclosure propose a non-transitory computer readable storage medium, on which a computer program is stored, which computer program, when being executed by a processor, carries out the steps of the method of determining an aero-engine air system characteristic according to any of the embodiments.
Drawings
The drawings that are required for use in the description of the embodiments or the related art will be briefly described below. The present disclosure will be more clearly understood from the following detailed description with reference to the accompanying drawings.
It will be apparent to those of ordinary skill in the art that the drawings in the following description are merely examples of the disclosure and that other drawings may be derived from them without inventive faculty.
FIG. 1 illustrates a flow diagram of a method of determining air system characteristics of an aircraft engine according to some embodiments of the present disclosure.
FIG. 2 illustrates a flow diagram of a method of determining characteristics of an aircraft engine air system in accordance with further embodiments of the present disclosure.
FIG. 3 illustrates a flow diagram of a method of constructing a predictive model for predicting air system temperature in accordance with some embodiments of the present disclosure.
Fig. 4 illustrates a schematic diagram of the relationship between the temperature of an air system and the high pressure compressor outlet temperature in accordance with some embodiments of the present disclosure.
Fig. 5 illustrates a schematic diagram of the temperature rise per unit time versus time for an air system according to some embodiments of the present disclosure.
FIG. 6 illustrates a flow diagram of a method of predicting a temperature of an air system of an aircraft engine high speed stage according to some embodiments of the present disclosure.
Fig. 7 shows a schematic diagram of the temperature of an air system predicting a high speed phase of an aircraft engine according to an application of the present disclosure.
FIG. 8 illustrates a flow diagram of a method of constructing a predictive model for predicting air system pressure and a method of predicting air system pressure for a high speed stage of an aircraft engine in accordance with some embodiments of the present disclosure.
Fig. 9 illustrates a schematic diagram of the relationship between the pressure of an air system and the high pressure compressor outlet pressure in accordance with some embodiments of the present disclosure.
FIG. 10 is a schematic structural view of an apparatus for determining characteristics of an aircraft engine air system according to some embodiments of the present disclosure.
Detailed Description
The technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure.
Unless specifically stated otherwise, the descriptions of "first," "second," "third," etc. in this disclosure are used for distinguishing between different objects and not for indicating a meaning of size or timing, etc.
Aviation in various embodiments of the present disclosureThe rotational speed of the engine may be, for example, a physical rotational speed or a relative conversion rotational speed. The physical rotational speed is converted to obtain a relative converted rotational speed. Based on the physical rotation speed N and the corresponding inlet temperature Tt of the high-pressure compressor 25 Calculating to obtain the converted rotating speed N of the high-pressure compressor 25R ＝N/sqrt(Tt 25 288.15); according to the physical rotation speed N of the preset design point _ds And the corresponding high pressure compressor inlet temperature Tt 25_ds Calculating the converted rotation speed N of the design point 25R_ds ＝N _ds /sqrt (tt25_ds/288.15); according to the conversion rotation speed N of the high-pressure compressor 25R And the converted rotational speed N of the design point 25R_ds Calculating to obtain relative conversion rotation speed N of physical rotation speed N 25R_relative ＝N 25R /N 25R_ds 。
FIG. 1 illustrates a flow diagram of a method of determining air system characteristics of an aircraft engine according to some embodiments of the present disclosure.
As shown in fig. 1, the method of this embodiment includes:
in step 110, a predictive model of air system characteristics representing a law of variation of the air system characteristics is constructed based on the characteristic test data of the air system at a low rotational speed stage of the aircraft engine.
In step 120, the characteristic data of the air system of the high speed phase of the aircraft engine is predicted using the prediction model.
Wherein the rotational speed of the aero-engine in the high rotational speed stage is greater than the rotational speed in the low rotational speed stage. The present disclosure does not limit the rotational speed range of the high rotational speed stage or the rotational speed range of the low rotational speed stage.
And (3) finding out a characteristic change rule of the air system by utilizing characteristic test data of the air system in a low-rotation-speed stage of the aero-engine, constructing a corresponding prediction model, and obtaining the characteristic data of the air system in a high-rotation-speed stage of the aero-engine through prediction.
When the air system includes a plurality of chambers, the method of steps 110-120 is performed separately for each chamber, thereby predicting characteristic data for each chamber of the air system. Specifically, as shown in fig. 2, the method for determining the air system characteristics of the aero-engine according to the embodiment includes:
in step 210, a predictive model of the characteristics of any chamber of the air system is constructed that represents the law of variation of the characteristics of that chamber of the air system based on the characteristics test data of that chamber of the air system during the low speed phase of the aircraft engine.
In step 220, the characteristic data of the chamber of the air system of the high speed phase of the aircraft engine is predicted using the prediction model.
Under the condition that the characteristic data of a certain chamber of the air system in the high-rotating-speed stage of the aeroengine is difficult to obtain through testing in practice, the characteristic test data of the chamber of the air system in the low-rotating-speed stage of the aeroengine is utilized to find the characteristic change rule of the chamber of the air system, a corresponding prediction model is constructed, and the characteristic data of the chamber of the air system in the high-rotating-speed stage of the aeroengine is obtained through prediction.
It can be seen that the method of predicting the characteristics of an air system and predicting the characteristics of a chamber of an air system are consistent, and the method of predicting the characteristics of an air system is equally applicable to predicting the characteristics of a chamber of an air system. In order to make the description more compact, the characteristics of the prediction air system or the characteristics of a certain chamber of the prediction air system are not distinguished in the following.
The characteristic parameters of the air system include, for example, temperature, pressure, etc., and the method of predicting the temperature and pressure, respectively, of the air system during the high rotational speed phase of an aircraft engine is described below.
FIG. 3 illustrates a flow diagram of a method of constructing a predictive model for predicting air system temperature in accordance with some embodiments of the present disclosure.
As shown in fig. 3, the method of this embodiment includes:
in step 310, characteristic test data of a reference local history of a low rotational speed phase of the aeroengine is obtained, where the reference local history includes: the characteristic test data related to temperature prediction comprise: the temperature of the air system and the outlet temperature of the high-pressure compressor in the low-speed rising stage of the aero-engine, the unit time temperature rising amount of the air system in the low-speed stable stage of the aero-engine, the temperature change amount delta T0 of the air system in the low-speed stable stage of the aero-engine and the like.
As can be seen from the schematic diagram of the relationship between the temperature of the air system (comprehensive coordinates) and the outlet temperature of the high-pressure compressor (abscissa coordinates) shown in fig. 4, a linear relationship is shown between the temperature of the air system and the outlet temperature of the high-pressure compressor in the rotational speed rising stage of each local process, and accordingly, a first prediction model is constructed.
In step 320, a first prediction model using the temperature of the high-pressure compressor outlet as an independent variable and the temperature of the air system as a dependent variable is constructed by fitting a relation curve between the temperature of the air system and the temperature of the high-pressure compressor outlet according to test data of the temperature of the air system and the temperature of the high-pressure compressor outlet in a low-rotation-speed rising stage of the aeroengine.
The first predictive model is, for example, a linear relationship model, formulated as follows:
y1＝a1×x1+b1
where y1 represents the temperature of the air system as a dependent variable, x1 represents the high pressure compressor outlet temperature as a dependent variable, and a1 and b1 are constants of the linear relationship model determined by the test data.
As can be seen from the schematic diagram of the relationship between the temperature rise per unit time (comprehensive coordinates) and time (abscissa) of the air system shown in fig. 5, the logarithmic relationship between the temperature rise per unit time and time of the air system is shown in the rotational speed plateau of each local course, and accordingly, the second prediction model is constructed. In addition, fig. 5 shows the temperature of the air system as a function of time in the rotational speed plateau of the respective partial course, as a continuous curve lying further up in fig. 5.
In step 330, a relationship curve of the temperature rise per unit time and time of the air system is fitted according to the test data of the temperature rise per unit time of the air system in the low-rotation-speed stable stage of the aero-engine, and a second prediction model taking time as an independent variable and taking the temperature rise per unit time of the air system as an independent variable is constructed.
The second prediction model is, for example, a logarithmic relationship model, and the formula is as follows:
y2＝a2×lnx2+b2
where y2 represents the temperature rise per unit time of the air system as an independent variable, x2 represents the time as an independent variable, and a2 and b2 are constants of a logarithmic relation model determined by test data.
In step 340, the first predictive model and the second predictive model are used as predictive models for predicting the air system temperature of the high speed phase of the aircraft engine.
And constructing a prediction model based on the characteristic test data of the low-rotation-speed stage of the aero-engine, and predicting the temperature of an air system of the high-rotation-speed stage of the aero-engine.
FIG. 6 illustrates a flow diagram of a method of predicting a temperature of an air system of an aircraft engine high speed stage according to some embodiments of the present disclosure.
As shown in fig. 6, the method of this embodiment includes:
in step 610, a predicted target for a set high speed phase of the aircraft engine is obtained, wherein the high speed phase of the aircraft engine includes at least one local history to be predicted, the predicted target includes a target speed of the aircraft engine and a target settling time at the target speed, the test history includes a reference local history 0 and at least one local history to be predicted, and the temperature prediction related characteristic test data is described with reference to step 310.
In step 620, a temperature Tn of the air system corresponding to the target rotational speed is determined based on the first predictive model and the high pressure compressor outlet temperature corresponding to the target rotational speed.
And inputting the outlet temperature of the high-pressure compressor corresponding to the target rotating speed as the value of the independent variable into a first prediction model, and outputting the value of the corresponding dependent variable as the temperature Tn of the air system corresponding to the target rotating speed.
The determination of the outlet temperature of the high-pressure compressor corresponding to the target rotational speed may be made by referring to the prior art, and will be described only briefly herein. And matching to obtain the temperature of the high-pressure compressor outlet at the target rotating speed based on the energy, flow, pressure and rotating speed balance equation by using the overall characteristic simulation model of the aero-engine.
In step 630, according to the second prediction model, the temperature variation Δti of the air system in the high-speed stationary phase of the aeroengine in each local process i to be predicted and the temperature variation Δtn' of the air system in the target stationary time in the high-speed stationary phase of the aeroengine in the local process n to be predicted where the target speed is located are determined by combining the test process and the target stationary time, wherein the local process i to be predicted is set as the local process to be predicted between the reference local process 0 and the local process n to be predicted where the target speed is located.
According to the test process, the duration time of the high-rotation-speed stable stage of the aeroengine in each local process i to be predicted is used as the value of an independent variable, the second prediction model is respectively input, and the value of the corresponding dependent variable is respectively output as each delta Ti.
According to the test history, the target stabilization time on the target rotating speed is used as the value of the independent variable, the second prediction model is input, and the value of the corresponding dependent variable is output as delta Tn'.
At step 640, a corresponding predicted temperature of the air system at the predicted target is determined based on Tn, ΔT0, each ΔTi, and ΔTn'.
The accumulated value of Tn, ΔT0, each ΔTi and ΔTn' is determined as the corresponding predicted temperature of the air system at the predicted target.
In some embodiments, n ranges from 1 to 3. Therefore, the characteristic test data of low rotating speed with small rotating speed difference is used as much as possible to predict the temperature data of high rotating speed, the characteristic test data of too low rotating speed is avoided to predict the temperature data of too high rotating speed as much as possible, and the accuracy of prediction is further improved.
Under the condition that the temperature of the air system in the high-speed stage of the aeroengine is difficult to obtain through testing in practice, the temperature change rule of the air system is found by utilizing characteristic test data related to the temperature prediction of the air system in the low-speed stage of the aeroengine, a corresponding prediction model is constructed, and the temperature data of the air system in the high-speed stage of the aeroengine is obtained through prediction.
An example of the application of temperature prediction is listed below, as shown in fig. 7.
Assuming that the temperature variation deltat 0 of the air system in the low rotational speed plateau with the relative converted rotational speed of 0.9 in the reference local history is obtained by the test, the predicted target includes the target rotational speed of the aircraft engine being 0.95 relative converted rotational speed and the target settling time at the target rotational speed being 0 seconds(s) and 190 seconds, the predicted target further includes the relative converted rotational speed being 1, and the target settling time at the target rotational speed being 0 seconds. Wherein, if the target stable time at the target rotation speed is 0 seconds, it indicates that the transient temperature needs to be predicted, and if the target stable time at the target rotation speed is greater than 0 seconds, it indicates that the steady temperature needs to be predicted.
First, characteristic test data of a reference local history (relative converted rotational speed from 0.85 to 0.9), such as a temperature variation Δt0 of an air system in a low rotational speed plateau of an aircraft engine (relative converted rotational speed stabilized at 0.9), etc., are obtained through a test, specifically referring to the description of step 310.
Then, according to the test data of the temperature of the air system and the outlet temperature of the high-pressure compressor in the low-rotation-speed rising stage (the relative conversion rotation speed is increased from 0.85 to 0.9) of the aero-engine, a relation curve of the temperature of the air system and the outlet temperature of the high-pressure compressor is fitted, and a first prediction model taking the outlet temperature of the high-pressure compressor as an independent variable x1 and the temperature of the air system as an independent variable y1 is constructed, wherein y1=0.7135x1+94.05.
Then, according to the test data of the temperature rise per unit time of the air system in the low-rotation-speed stable stage (the relative conversion rotation speed is stabilized at 0.9) of the aero-engine, a relation curve of the temperature rise per unit time of the air system and time is fitted, and a second prediction model with time as an independent variable x2 and the temperature rise per unit time of the air system as a dependent variable y2 is constructed, wherein y2= -0.0144lnx1+0.0744.
Next, for the predicted target (relative conversion rotation speed of 0.95, target stabilization time of 0 seconds or 190 seconds):
and determining the temperature T0 of the air system corresponding to the target rotating speed 0.95 according to the high-pressure compressor outlet temperature corresponding to the first predictive model y1=0.7135x1+94.05 and the target rotating speed 0.95.
According to the second prediction model y2= -0.0144lnx1+0.0744, combining the test course and the target stable time, determining the temperature change delta T1 'of the air system in the target stable time (190 seconds) at the high-rotation-speed stable stage (the relative conversion rotation speed is stabilized at 0.95) of the aeroengine in the local course 1 to be predicted, where the target rotation speed is located, if the target stable time is 0 seconds, the delta T1' =0.
Therefore, the predicted temperature of the air system at the predicted target (relative converted rotational speed of 0.95, target settling time of 0 seconds) is: t0+t0.
Therefore, the predicted temperature of the air system at the predicted target (relative converted rotational speed of 0.95, target settling time of 190 seconds) is: t0+t0+Δt1'.
Finally, for the predicted target (relative converted rotational speed of 1, target settling time of 0 seconds):
and determining the temperature T1 of the air system corresponding to the target rotating speed 1 according to the first prediction model y1=0.7135x1+94.05 and the outlet temperature of the high-pressure compressor corresponding to the target rotating speed 1.
According to a second predictive model y2= -0.0144lnx1+0.0744, combining the test history and the target stabilization time, determining the temperature change delta T1 of the air system in the overall stabilization time (determined according to the test history) during the high-rotation-speed stabilization phase (the relative conversion rotation speed stabilized at 0.95) of the aeroengine.
Therefore, the predicted temperature of the air system at the predicted target (relative converted rotational speed of 1, target settling time of 0 seconds) is: t1+t0+t1.
The temperature prediction results for a certain chamber of the air system are as follows:
TABLE 1
FIG. 8 illustrates a flow diagram of a method of constructing a predictive model for predicting air system pressure (steps 810-820) and a method of predicting air system pressure for a high speed stage of an aircraft engine (steps 830-840) in accordance with some embodiments of the present disclosure.
As shown in fig. 8, the method of this embodiment includes:
in step 810, characteristic test data of a reference local history of a low speed phase of the aeroengine is obtained, and the characteristic test data related to pressure prediction comprises: the pressure of the air system in the reference local process, the outlet pressure of the high-pressure compressor and the like.
As can be seen from the schematic diagram of the relationship between the pressure of the air system (comprehensive coordinates) and the outlet pressure of the high-pressure compressor (abscissa) shown in fig. 9, a linear relationship is shown between the pressure of the air system and the outlet pressure of the high-pressure compressor, and a third prediction model is constructed according to this.
In step 820, a third prediction model using the high-pressure compressor outlet pressure as an independent variable and the air system pressure as a dependent variable is constructed by fitting a relation curve between the air system pressure and the high-pressure compressor outlet pressure according to the test data of the air system pressure and the high-pressure compressor outlet pressure in the reference local process, and the third prediction model is used as a prediction model for predicting the air system pressure.
The third predictive model is, for example, a linear relationship model, formulated as:
y3＝a3×x3+b3
where y3 represents the pressure of the air system as a dependent variable, x3 represents the high pressure compressor outlet pressure as a dependent variable, and a3 and b3 are constants of the linear relationship model determined by the test data.
In step 830, a predicted target for the set high speed phase of the aircraft engine is obtained, wherein the predicted target comprises a target speed of the aircraft engine.
In step 840, a pressure of the air system corresponding to the target rotational speed is determined based on the third predictive model and the high pressure compressor outlet pressure corresponding to the target rotational speed.
And inputting the outlet pressure of the high-pressure compressor corresponding to the target rotating speed as the value of the independent variable into a third prediction model, and outputting the value of the corresponding dependent variable as the pressure of the air system corresponding to the target rotating speed.
The determination of the corresponding high-pressure compressor outlet pressure for the target rotational speed may be made by reference to the prior art, and will be described only briefly herein. And matching the pressure of the high-pressure compressor outlet at the target rotating speed based on the energy, flow, pressure and rotating speed balance equation by using the overall characteristic simulation model of the aero-engine.
And constructing a prediction model based on the characteristic test data of the low-rotation-speed stage of the aero-engine, and predicting the pressure of an air system of the high-rotation-speed stage of the aero-engine. Under the condition that the pressure of the air system in the high-speed stage of the aeroengine is difficult to obtain through testing in practice, the pressure change rule of the air system is found by utilizing characteristic test data related to pressure prediction of the air system in the low-speed stage of the aeroengine, a corresponding prediction model is constructed, and the pressure data of the air system in the high-speed stage of the aeroengine is obtained through prediction.
An example of application of the pressure prediction is listed below.
Assume that: the third prediction model fitted according to the change rule of the pressure test data of the relative conversion rotating speed increasing from 0 to 0.9 is y=0.6359x+16.09, the corresponding high-pressure compressor outlet pressure of the target rotating speed (such as 0.95,1 and the like) to be predicted is taken as the value of an independent variable to be input into the third prediction model, and the value of the corresponding dependent variable (such as 702, 959 and the like) is taken as the pressure of the air system corresponding to the target rotating speed.
The pressure prediction for a certain chamber of the air system is as follows:
TABLE 2
FIG. 10 is a schematic structural view of an apparatus for determining characteristics of an aircraft engine air system according to some embodiments of the present disclosure.
As shown in fig. 10, the apparatus 1000 of this embodiment includes: a memory 1010 and a processor 1020 coupled to the memory 1010, the processor 1020 being configured to perform the method of determining an aero-engine air system characteristic in any of the foregoing embodiments based on instructions stored in the memory 1010.
For example, based on the characteristic test data of the air system in the low-rotation-speed stage of the aero-engine, constructing a prediction model of the air system characteristic representing the characteristic change rule of the air system; and predicting characteristic data, such as temperature, pressure and the like, of the air system at the high rotating speed stage of the aero-engine by using the prediction model. The specific method of constructing the temperature prediction model and predicting the temperature, constructing the pressure prediction model and predicting the pressure refers to the foregoing embodiment, and will not be described herein.
The memory 1010 may include, for example, system memory, fixed nonvolatile storage media, and the like. The system memory stores, for example, an operating system, application programs, boot Loader (Boot Loader), and other programs.
The apparatus 1000 may also include an input-output interface 1030, a network interface 1040, a storage interface 1050, and the like. These interfaces 1030, 1040, 1050 and the memory 1010 and processor 1020 may be connected by, for example, a bus 1060. The input/output interface 1030 provides a connection interface for input/output devices such as a display, a mouse, a keyboard, a touch screen, and the like. Network interface 1040 provides a connection interface for a variety of networking devices. Storage interface 1050 provides a connection interface for external storage devices such as SD cards, U-discs, and the like.
The disclosed embodiments also propose a non-transitory computer-readable storage medium, on which a computer program is stored, which computer program, when being executed by a processor, carries out the steps of the method of determining an aeroengine air system characteristic of any of the embodiments.
For example, based on the characteristic test data of the air system in the low-rotation-speed stage of the aero-engine, constructing a prediction model of the air system characteristic representing the characteristic change rule of the air system; and predicting characteristic data, such as temperature, pressure and the like, of the air system at the high rotating speed stage of the aero-engine by using the prediction model. The specific method of constructing the temperature prediction model and predicting the temperature, constructing the pressure prediction model and predicting the pressure refers to the foregoing embodiment, and will not be described herein.
It will be appreciated by those skilled in the art that embodiments of the present disclosure may be provided as a method, system, or computer program product. Accordingly, the present disclosure may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present disclosure may take the form of a computer program product embodied on one or more non-transitory computer-readable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) having computer program code embodied therein.
The present disclosure is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the disclosure. It will be understood that each flowchart and/or block of the flowchart illustrations and/or block diagrams, and combinations of flowcharts and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
The foregoing description of the preferred embodiments of the present disclosure is not intended to limit the disclosure, but rather to enable any modification, equivalent replacement, improvement or the like, which fall within the spirit and principles of the present disclosure.
Claims (12)
1. A method of determining characteristics of an aircraft engine air system, comprising:
based on the characteristic test data of the air system in the low-rotation-speed stage of the aero-engine, constructing a prediction model of the air system characteristic representing the characteristic change rule of the air system;
predicting characteristic data of an air system at a high rotating speed stage of the aero-engine by using the prediction model;
the low speed phase of the aeroengine comprises a reference local history comprising: a low rotational speed rising stage of the aero-engine and a low rotational speed stabilizing stage of the aero-engine;
constructing the prediction model, including:
according to the test data of the temperature of the air system and the outlet temperature of the high-pressure compressor in the low-rotation-speed rising stage of the aero-engine, a first prediction model taking the outlet temperature of the high-pressure compressor as an independent variable and taking the temperature of the air system as an independent variable is constructed;
according to the test data of the temperature rise of the air system in unit time of the low-rotation-speed stable stage of the aero-engine, constructing a second prediction model taking time as an independent variable and taking the temperature rise of the air system in unit time as a dependent variable;
and taking the first prediction model and the second prediction model as prediction models for predicting the temperature of the air system.
2. The method of claim 1, wherein the first predictive model is a linear relationship model; the second predictive model is a logarithmic relationship model.
3. The method of claim 1, wherein predicting the characteristic data of the air system for the high speed phase of the aircraft engine comprises:
obtaining a set prediction target and a test history of an aero-engine high-speed stage, wherein the aero-engine high-speed stage comprises at least one local history to be predicted, the prediction target comprises a target speed of the aero-engine and a target stable time on the target speed, the test history comprises a reference local history 0 and at least one local history to be predicted, and the characteristic test data also comprises a temperature change delta T0 of an air system in a low-speed stable stage of the aero-engine;
determining the temperature Tn of the air system corresponding to the target rotating speed according to the first prediction model and the outlet temperature of the high-pressure compressor corresponding to the target rotating speed;
according to the second prediction model, combining a test course and a target stabilization time, determining a temperature change delta Ti of an air system in a high-speed stable stage of the aeroengine in each local course i to be predicted and a temperature change delta Tn' of the air system in a target stabilization time in a high-speed stable stage of the aeroengine in a local course n to be predicted in which the target speed is positioned, wherein the local course i to be predicted is a local course to be predicted between a reference local course 0 and the local course n to be predicted in which the target speed is positioned;
and determining the corresponding predicted temperature of the air system at the predicted target according to Tn, deltaT 0, deltaTi and deltaTn'.
4. A method according to claim 3, wherein determining Δti and Δtn' comprises:
according to the test process, respectively inputting the duration time of the high-rotation-speed stable stage of the aeroengine in each local process i to be predicted into the second prediction model, and respectively outputting each DeltaTi;
and inputting the target stable time on the target rotating speed into the second prediction model according to the test process, and outputting delta Tn'.
5. The method of claim 3, wherein the step of,
the accumulated values of Tn, ΔT0, ΔTi and ΔTn' are determined as the corresponding predicted temperatures of the air system at the predicted targets.
6. A method according to claim 3, wherein n ranges from 1 to 3.
7. The method of claim 1, wherein the low rotational speed phase of the aircraft engine comprises a baseline local history;
constructing the prediction model, including:
and constructing a third prediction model which takes the outlet pressure of the high-pressure compressor as an independent variable and the pressure of the air system as a dependent variable according to test data of the pressure of the air system and the outlet pressure of the high-pressure compressor in the reference local process, and taking the third prediction model as a prediction model for predicting the pressure of the air system.
8. The method of claim 7, wherein the third predictive model is a linear relationship model.
9. The method of claim 7, wherein predicting the characteristic data of the air system for the high speed phase of the aircraft engine comprises:
acquiring a predicted target of a set high-speed stage of the aero-engine, wherein the predicted target comprises a target speed of the aero-engine;
and determining the pressure of the air system corresponding to the target rotating speed according to the third prediction model and the outlet pressure of the high-pressure compressor corresponding to the target rotating speed.
10. The method of claim 1, wherein the step of determining the position of the substrate comprises,
the characteristic test data is characteristic test data of a chamber of the air system;
the predictive model is a predictive model of a characteristic of the chamber of the air system;
the predicted characteristic data is characteristic data of the chamber of the air system of the high rotational speed phase of the aircraft engine.
11. An apparatus for determining characteristics of an aircraft engine air system, comprising:
a memory; and a processor coupled to the memory, the processor configured to perform the method of determining an aeroengine air system characteristic of any of claims 1-10 based on instructions stored in the memory.
12. A non-transitory computer readable storage medium having stored thereon a computer program which, when executed by a processor, implements the steps of the method of determining aero engine air system characteristics of any of claims 1-10.
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