CN114692309B - Real-time calculation method for axial force of low-pressure turbine rotor of aviation turbofan engine - Google Patents
Real-time calculation method for axial force of low-pressure turbine rotor of aviation turbofan engine Download PDFInfo
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Abstract
The application provides a real-time calculation method for axial force of a low-pressure turbine rotor of an aeroengine, which comprises the following steps: determining main section parameters of the aeroengine and related parameters with strong relevance to axial force of a low-pressure turbine rotor runner; acquiring sample data of the main section parameters and related parameters; fitting according to the sample data to obtain a flow passage axial force calculation model; correcting the expansion ratio of the low-pressure turbine according to the performance parameter test data of the main runner in the actual test of the engine; correcting the fitted flow channel axial force calculation model; determining an inner cavity axial force key parameter and an inner cavity axial force non-key parameter and corresponding axial projection area coefficients of the engine in a cold state; calculating the area variation of each inner cavity and the thermal state area deformation correction area coefficient of the inner cavity; building an inner cavity axial force calculation model: and combining the corrected flow passage axial force calculation model and the inner cavity axial force calculation model to obtain a low-pressure turbine rotor axial force calculation model.
Description
Technical Field
The application belongs to the technical field of aero-engine design, and particularly relates to a real-time calculation method for axial force of a low-pressure turbine rotor of an aero-turbofan engine.
Background
During operation of the dual-rotor turbofan engine, the low-pressure turbine rotor component can bear certain pneumatic axial load, and the size of the low-pressure turbine rotor component directly influences the strength life of the component and indirectly influences the reliability of the low-pressure rotor thrust bearing. In the whole machine test, the temperature of the component is higher, the structural deformation is larger, and the performance parameters of the inlet and outlet cross sections are difficult to measure, so that the design value of the performance parameters of the component cannot be corrected, and the design error is larger.
The existing method for calculating the axial force of the low-pressure turbine rotor of the turbofan engine obtains an axial force result by inputting the performance parameters of the inlet and outlet of the low-pressure turbine rotor blade, the pressure parameters of each related inner cavity of an air system and the pressure parameters of the inner cavities of bearings related to an lubricating oil system into a cold state structure model. The method has the advantages that the input parameters are multiple (more than 20 single-stage low-pressure turbines are needed, more than 30 double-stage low-pressure turbines are needed, the parameters are increased along with the increase of the stages), the error is large, the calculation model is greatly different from the actual model, the calculation efficiency is low, the calculated input parameters cannot be provided in real time, and therefore the calculation and output of the axial force of the low-pressure turbine rotor cannot be carried out in real time in the whole machine test.
Disclosure of Invention
The purpose of the application is to provide a real-time calculation method for axial force of a low-pressure turbine rotor of an aeroengine, so as to solve or alleviate at least one problem in the background art.
The technical scheme of the application is as follows: a real-time calculation method for axial force of a low-pressure turbine rotor of an aeroengine comprises the following steps:
determining main section parameters of the aeroengine;
and determining a related parameter with stronger relevance to the axial force of the low-pressure turbine rotor flow passage from the main section parameters, wherein the related parameter with stronger relevance is as follows: total pressure at the outlet of the compressor and total pressure at the outlet of the connotation;
acquiring sample data of the main section parameters and related parameters;
fitting according to the sample data to obtain a flow passage axial force calculation model;
correcting the expansion ratio of the low-pressure turbine according to the performance parameter test data of the main runner in the actual test of the engine;
correcting the fitted flow channel axial force calculation model;
determining a critical parameter of the axial force of the inner cavity and a non-critical parameter of the axial force of the inner cavity, wherein the critical parameter of the axial force of the inner cavity comprises a critical inner cavity and a critical inner cavity pressure, and the non-critical parameter of the axial force of the inner cavity comprises a non-critical inner cavity and a non-critical inner cavity pressure;
determining the axial projection area coefficients of the engine corresponding to the key inner cavity and the non-key inner cavity in a cold state;
calculating radial thermal deformation of the inner diameter and the outer diameter of each inner cavity structure in each working state to obtain the area variation of each inner cavity;
correcting the area coefficient according to the structural thermal state area deformation of the key inner cavity and the non-key inner cavity;
building an inner cavity axial force calculation model:
and combining the corrected flow passage axial force calculation model and the inner cavity axial force calculation model to obtain a low-pressure turbine rotor axial force calculation model.
Further, the main section parameters include: total temperature T of fan inlet 2 Total pressure P of fan inlet 2 Total pressure P of fan inlet 13 Total inlet temperature T of air compressor 25 Total internal pressure P of inlet of compressor 23 Total temperature T of compressor outlet 3 Total pressure P at compressor outlet 3 Total internal culvert outlet temperature T 6 Total pressure P of connotation outlet 6 Total temperature T of culvert outlet 16 Total pressure P of outlet of culvert 16 。
Further, in the process of obtaining the flow channel axial force calculation model by fitting according to the sample data, the fitting form is a quadratic polynomial, namely: y=ax 2 +bx+c
Wherein a and b are polynomial coefficients, c is a constant, and coefficients and constants obtained by fitting different engines are different;
j is a conversion coefficient, and the values of different engines are different;
g is a conversion coefficient, and the values of different engines are different;
the fitted flow channel axial force calculation model after finishing is as follows:
further, the low pressure turbine expansion ratio satisfies: pi * ＝k·π
Wherein: pi * In order to correct the expansion ratio, pi is the expansion ratio before correction, and k is the correction coefficient.
Further, the value range of the correction coefficient k is 1 to 1.3.
Further, the corrected fitted flow channel axial force calculation model F A * The method comprises the following steps:
further, the method for determining the key parameters of the axial force of the inner cavity and the non-key parameters of the axial force of the inner cavity comprises the following steps:
determining a key inner cavity and a non-key inner cavity according to whether the inner cavity pressure can be measured, the size of the axial projection area of the inner cavity and the pressure, and if the inner cavity pressure can be measured, the axial projection area of the inner cavity is large and the pressure is large, determining the inner cavity as the key inner cavity;
and vice versa, is a non-critical lumen.
Further, the non-critical lumen pressure has a correlation with the critical lumen pressure, the correlation satisfying the formula: p (P) fsfi ＝D i P fsgj +E i
Wherein: d (D) i Is a linear coefficient, E i Is a constant term, i is a non-critical lumen number, j is any critical lumen number, and is repeatable。
Further, the inner cavity axial force calculation model F B The method comprises the following steps:
wherein: a. b is a polynomial coefficient and c is a constant;
r is the key inner cavity number, and the values are sequentially 1, 2 and 3 … … m;
i is a non-key inner cavity number, and the values are sequentially 1, 2 and 3 … … n;
j is a key inner cavity number, has a value of any one of 1, 2 and 3 … … m, and can be repeated;
the area coefficient corresponding to the corrected key inner cavity corresponding to the key inner cavity number r;
P dwgr key lumen pressure corresponding to key lumen number r;
P dwgj key lumen pressure corresponding to key lumen number j;
the area coefficient corresponding to the non-critical inner cavity after correction corresponding to the non-critical inner cavity number i;
P dwgi non-critical lumen pressures corresponding to non-critical lumen number i.
Further, the low-pressure turbine rotor axial force calculation model F dw The method comprises the following steps:
wherein J, G is a conversion coefficient.
According to the novel low-pressure turbine rotor axial force calculation method, the relevance between the screening and the low-pressure turbine rotor runner axial force is strong, the difference between the actual value and the theoretical design value of the low-pressure turbine expansion ratio is considered while the main section parameter and the related parameter data sample of the engine which can be measured in the whole machine test are fitted, and the axial force model is corrected according to the thermal deformation result of the low-pressure turbine rotor structure, so that a novel low-pressure turbine rotor axial force calculation model is obtained, all input parameters in the calculation model can be obtained in real time in the whole machine test of the engine, therefore, the axial force value of the low-pressure turbine rotor can be calculated in real time, the rotor axial force of the component is monitored in real time, and the abnormal condition of the key parameter is found in time.
Compared with the existing engine axial force calculation method, the low-pressure turbine rotor axial force meter real-time calculation method can reduce calculation workload, simplify a model, facilitate and fast calculation process, reduce calculation errors, and finally observe the value condition of the low-pressure turbine rotor axial force in the whole machine test process in real time.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a flow chart of a method for real-time calculation of axial force of a low pressure turbine rotor of an aircraft turbofan engine according to the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
As shown in fig. 1, the method for calculating the axial force of the low-pressure turbine rotor of the aviation turbofan engine in real time comprises the following steps:
1. determining main section parameters of engine
The main section parameters of the engine which can be measured in the whole engine test comprise: total temperature T of fan inlet 2 Total pressure P of fan inlet 2 Total pressure P of fan inlet 13 Total inlet temperature T of air compressor 25 Total internal pressure of inlet of air compressorP 23 Total temperature T of compressor outlet 3 Total pressure P at compressor outlet 3 Total internal culvert outlet temperature T 6 Total pressure P of connotation outlet 6 Total temperature T of culvert outlet 16 Total pressure P of outlet of culvert 16 。
2. Determining a relevant parameter with stronger relevance to the axial force of the low-pressure turbine rotor runner, wherein the relevant parameter with stronger relevance is as follows: total pressure P at outlet of compressor 3 Total pressure P of connotation outlet 6 。
3. According to the primary section parameters and the data samples of the related parameters of the axial force of the flow channel, a flow channel axial force calculation model Fa is obtained through preliminary fitting, and the fitting form is a quadratic polynomial: y=ax 2 +bx+c
Wherein: a. b is a polynomial coefficient, c is a constant, and coefficients and constants obtained by fitting different engines are different;
j is a conversion coefficient, and the values of different engines are different;
g is a conversion coefficient, and the values of different engines are different;
the fitted flow channel axial force calculation model after finishing is as follows:
for example, table 1 is a data sample of the main section parameters and the flow channel axial force related parameters in an embodiment of the present application.
TABLE 1 data sample of parameters relating to the principal cross-section parameters and axial force of the flow channels
The flow channel axial force calculation model obtained by fitting the main section parameters and the flow channel axial force related parameter data samples in table 1 is as follows:
4. correcting low-pressure turbine expansion ratio
And correcting the low-pressure turbine expansion ratio according to the test data of the performance parameters of the main runner in the actual test of the engine, and meeting the following conditions: pi * ＝k·π
Wherein: pi * In order to correct the expansion ratio, pi is the expansion ratio before correction, and k is the correction coefficient, wherein the value range of the correction coefficient k is usually 1-1.3, and the values of different engines are different according to actual test conditions.
5. Correcting and fitting to obtain a flow channel axial force calculation model F A * The method comprises the following steps:
in the embodiment, according to the performance parameter test condition of the main runner in the actual test of the engine, the correction coefficient of the expansion ratio of the low-pressure turbine is 1.2, and the corrected fitted runner axial force calculation model is as follows:
6. determining correlations between critical and non-critical parameters and other parameters of low pressure turbine rotor inner cavity axial force
And determining a key inner cavity and a non-key inner cavity according to whether the pressure of the inner cavity of the rotor can be measured, the size of the axial projection area and the pressure, wherein the key inner cavity is an inner cavity with large pressure and the pressure can be measured, and the key inner cavity is a non-key inner cavity. It is understood that the positions of critical and non-critical internal cavities of different engines may be different.
For example, in the present application the practiceIn an embodiment, the key lumens determined by the above procedure are respectively: g1, g2, g3, g4, g5, g6, g7, and the key lumen pressures corresponding thereto are: p (P) dwg1 、P dwg2 、P dwg3 、P dwg4 、P dwg5 、P dwg6 、P dwg7 The method comprises the steps of carrying out a first treatment on the surface of the The non-critical lumens determined by the above procedure were: f1, f2, f3, f4, the corresponding non-critical lumen pressures are; p (P) dwf1 、P dwf2 、P dwf3 、P dwf4 。
The correlation of the non-critical and critical lumens satisfies: p (P) dwfi ＝D i ·P dwgj +E i 。
Wherein: i is a non-critical lumen number, j is any critical lumen number, and can be repeated; p (P) dwfi Corresponding non-critical lumen pressure, P, for non-critical lumen number i dwgj For the corresponding critical lumen pressure when the critical lumen number is j, D i For the linear coefficient corresponding to non-critical lumen number i, E i Constant terms corresponding to non-critical lumens numbered i.
In this embodiment of the present application, the non-critical and critical lumens have the following correlation:
P dwf1 ＝1.1·P dwg5 -3
P dwf2 ＝0.9·P dwg6 +1
P dwf3 ＝1.1·P dwg5 -2
P dwf4 ＝1.6·P dwg3 -8。
7. determining axial projection area coefficient of engine cold state corresponding to each inner cavity
Table 2 shows the cold state structural area coefficient table corresponding to each inner cavity in an embodiment of the present application.
TABLE 2 area coefficients of Cold Structure for lumens
In the table, L g Area system corresponding to key inner cavityNumber, L f Is the area coefficient corresponding to the non-critical cavity.
8. Determining thermal deformation of each cavity structure
And calculating the radial thermal deformation of the inner diameter and the outer diameter of each inner cavity structure under each working state to obtain the area change of each inner cavity.
Table 3 shows the amount of change in the area corresponding to the lumen parameter in this example of the present application.
TABLE 3 area variation (percent) for parameters of lumen
| Parameters of lumen | P dwf1 | P dwg1 | P dwf2 | P dwf3 | P dwg2 | P dwf4 |
| Area variation | +6％ | +2％ | +3％ | +2％ | +2％ | +32％ |
| Parameters of lumen | P dwg3 | P dwg4 | P dwg5 | P dwg6 | P dwg7 | |
| Area variation | +11％ | +4％ | +19％ | +2％ | +1％ |
9. And correcting the area coefficient according to the thermal state area deformation of the structure.
Table 4 shows the corrected area coefficient table in this example of the present application.
TABLE 4 area coefficient after correction
10. Inner cavity axial force calculation model F B The method comprises the following steps:
wherein: a. b is a polynomial coefficient and c is a constant;
r is the key inner cavity number, and the values are sequentially 1, 2 and 3 … … m;
i is a non-key inner cavity number, and the values are sequentially 1, 2 and 3 … … n;
j is a key inner cavity number, has a value of any one of 1, 2 and 3 … … m, and can be repeated;
the area coefficient corresponding to the corrected key inner cavity corresponding to the key inner cavity number r;
P dwgr key lumen pressure corresponding to key lumen number r;
P dwgj key lumen pressure corresponding to key lumen number j;
the area coefficient corresponding to the non-critical inner cavity after correction corresponding to the non-critical inner cavity number i;
P dwgi non-critical lumen pressures corresponding to non-critical lumen number i.
The axial force of the inner cavity under the embodiment of the application is as follows:
F B ＝-14.3P dwg1 -193.3P dwg2 -47.3P dwg3 +176.4P dwg4 -17.8P dwg5 +53.6P dwg6 +40.6P dwg7 +81。
11. combining the corrected flow passage axial force calculation model and the inner cavity axial force calculation model to obtain a low-pressure turbine rotor axial force calculation model F dw The method comprises the following steps:
wherein J, G is a conversion coefficient, and the values of different engines are different;
k is a correction coefficient of expansion ratio, the value range is 1-1.3, and the values of different engines are different according to actual test conditions;
r is the key inner cavity number, and the values are sequentially 1, 2 and 3 … … m;
i is a non-key inner cavity number, and the values are sequentially 1, 2 and 3 … … n;
j is the key inner cavity number, has any value of 1, 2 and 3 … … m, and can be repeated.
The low pressure turbine rotor axial force calculation model in this embodiment of the present application is ultimately:
finally, referring to tables 5 and 6, real-time test data of the complete machine test and real-time calculation results of the axial force of the low pressure turbine rotor in an embodiment of the present application are shown.
TABLE 5 real-time test data in kilopascals
| Time of day | P 3 | P 6 | P dwg1 | P dwg2 | P dwg3 | P dwg4 | P dwg5 | P dwg6 | P dwg7 |
| 00：01 | 670 | 120 | 110 | 200 | 110 | 120 | 120 | 150 | 120 |
| 00：02 | 970 | 200 | 150 | 280 | 170 | 180 | 180 | 200 | 180 |
| 00：03 | 1400 | 270 | 190 | 400 | 240 | 250 | 250 | 260 | 250 |
| 00：04 | 1700 | 300 | 230 | 450 | 270 | 280 | 280 | 290 | 280 |
Table 6 real time test data, unit cattle
| Time of day | F dw |
| 00：01 | -23452 |
| 00：02 | -29125 |
| 00：03 | -45475 |
| 00：04 | -58075 |
According to the novel low-pressure turbine rotor axial force calculation method, the relevance between the screening and the low-pressure turbine rotor runner axial force is strong, the difference between the actual value and the theoretical design value of the low-pressure turbine expansion ratio is considered while the main section parameter and the related parameter data sample of the engine which can be measured in the whole machine test are fitted, and the axial force model is corrected according to the thermal deformation result of the low-pressure turbine rotor structure, so that a novel low-pressure turbine rotor axial force calculation model is obtained, all input parameters in the calculation model can be obtained in real time in the whole machine test of the engine, therefore, the axial force value of the low-pressure turbine rotor can be calculated in real time, the rotor axial force of the component is monitored in real time, and the abnormal condition of the key parameter is found in time.
Compared with the existing engine axial force calculation method, the low-pressure turbine rotor axial force meter real-time calculation method can reduce calculation workload, simplify a model, facilitate and fast calculation process, reduce calculation errors, and finally observe the value condition of the low-pressure turbine rotor axial force in the whole machine test process in real time.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The real-time calculation method for the axial force of the low-pressure turbine rotor of the aeroengine is characterized by comprising the following steps of:
determining main section parameters of the aeroengine;
and determining a related parameter with stronger relevance to the axial force of the low-pressure turbine rotor flow passage from the main section parameters, wherein the related parameter with stronger relevance is as follows: total pressure at the outlet of the compressor and total pressure at the outlet of the connotation;
acquiring sample data of the main section parameters and related parameters;
fitting according to the sample data to obtain a flow passage axial force calculation model;
correcting the expansion ratio of the low-pressure turbine according to the performance parameter test data of the main runner in the actual test of the engine;
correcting the fitted flow channel axial force calculation model;
determining a critical parameter of the axial force of the inner cavity and a non-critical parameter of the axial force of the inner cavity, wherein the critical parameter of the axial force of the inner cavity comprises a critical inner cavity and a critical inner cavity pressure, and the non-critical parameter of the axial force of the inner cavity comprises a non-critical inner cavity and a non-critical inner cavity pressure;
determining the axial projection area coefficients of the engine corresponding to the key inner cavity and the non-key inner cavity in a cold state;
calculating radial thermal deformation of the inner diameter and the outer diameter of each inner cavity structure in each working state to obtain the area variation of each inner cavity;
correcting the area coefficient according to the structural thermal state area deformation of the key inner cavity and the non-key inner cavity;
building an inner cavity axial force calculation model:
and combining the corrected flow passage axial force calculation model and the inner cavity axial force calculation model to obtain a low-pressure turbine rotor axial force calculation model.
2. The method for real-time calculation of aeroengine low pressure turbine rotor axial force of claim 1, wherein said main section parameters comprise: total temperature T of fan inlet 2 Total pressure P of fan inlet 2 Total pressure P of fan inlet 13 Total inlet temperature T of air compressor 25 Total internal pressure P of inlet of compressor 23 Total temperature T of compressor outlet 3 Total pressure P at compressor outlet 3 Total internal culvert outlet temperature T 6 Total pressure P of connotation outlet 6 Total temperature T of culvert outlet 16 Total pressure P of outlet of culvert 16 。
3. The method for real-time calculation of axial force of low-pressure turbine rotor of aeroengine according to claim 2, wherein in the process of obtaining the flow channel axial force calculation model by fitting according to the sample data, the fitting form is a quadratic polynomial, namely: y=ax 2 +bx+c
Wherein a and b are polynomial coefficients, c is a constant, and coefficients and constants obtained by fitting different engines are different;
j is a changeCalculating coefficients, wherein the values of different engines are different;
g is a conversion coefficient, and the values of different engines are different;
the fitted flow channel axial force calculation model after finishing is as follows:
4. a method for real-time calculation of the axial force of the low pressure turbine rotor of an aircraft engine according to claim 3, wherein said low pressure turbine expansion ratio satisfies: pi * ＝k·π
Wherein: pi * In order to correct the expansion ratio, pi is the expansion ratio before correction, and k is the correction coefficient.
5. The method for calculating the axial force of the low-pressure turbine rotor of the aeroengine in real time according to claim 4, wherein the value range of the correction coefficient k is 1-1.3.
6. The method for calculating axial force of low-pressure turbine rotor of aero-engine in real time according to claim 4 or 5, wherein the corrected fitted flow channel axial force calculation model F A * The method comprises the following steps:
。
7. the method for calculating the axial force of the low-pressure turbine rotor of the aeroengine in real time according to claim 6, wherein the method for determining the key parameters of the axial force of the inner cavity and the non-key parameters of the axial force of the inner cavity is as follows:
determining a key inner cavity and a non-key inner cavity according to whether the inner cavity pressure can be measured, the size of the axial projection area of the inner cavity and the pressure, and if the inner cavity pressure can be measured, the axial projection area of the inner cavity is large and the pressure is large, determining the inner cavity as the key inner cavity;
and vice versa, is a non-critical lumen.
8. The method of real-time computation of axial force of a low pressure turbine rotor of an aircraft engine according to claim 7, wherein said non-critical internal cavity pressure has a correlation with said critical internal cavity pressure, said correlation satisfying the formula: p (P) fsfi ＝D i P fsgj +E i
Wherein: d (D) i Is a linear coefficient, E i Is a constant term, i is a non-critical lumen number, j is any critical lumen number, and is repeatable.
9. The method for real-time calculation of axial force of low-pressure turbine rotor of aeroengine as claimed in claim 7, wherein said internal cavity axial force calculation model F B The method comprises the following steps:
wherein: a. b is a polynomial coefficient and c is a constant;
r is the key inner cavity number, and the values are sequentially 1, 2 and 3 … … m;
i is a non-key inner cavity number, and the values are sequentially 1, 2 and 3 … … n;
j is a key inner cavity number, has a value of any one of 1, 2 and 3 … … m, and can be repeated;
the area coefficient corresponding to the corrected key inner cavity corresponding to the key inner cavity number r;
P dwgr key lumen pressure corresponding to key lumen number r;
P dwgj key lumen pressure corresponding to key lumen number j;
the area coefficient corresponding to the non-critical inner cavity after correction corresponding to the non-critical inner cavity number i;
P dwgi non-critical lumen pressures corresponding to non-critical lumen number i.
10. The method for real-time calculation of low pressure turbine rotor axial force for an aircraft engine according to claim 9, wherein said low pressure turbine rotor axial force calculation model F dw The method comprises the following steps:
wherein J, G is a conversion coefficient.
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| CN115680902B (en) * | 2022-10-13 | 2024-05-03 | 中国航发四川燃气涡轮研究院 | Method for adjusting axial force of aero-engine rotor |
| CN115935535B (en) * | 2022-11-10 | 2023-11-28 | 中国航发沈阳发动机研究所 | Large bypass ratio aero-engine low-pressure rotor fulcrum static load calculation method |
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