CN115372007B - Method and device for determining performance attenuation parameters of turbofan engine - Google Patents
Method and device for determining performance attenuation parameters of turbofan engine Download PDFInfo
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Abstract
The application belongs to the technical field of engine tests, and particularly relates to a method and a device for determining performance attenuation parameters of a turbofan engine. S1, acquiring engine characteristic data under different atmospheric temperature conditions; s2, regarding any atmospheric temperature, taking the exhaust temperature as a limiting value, and acquiring a plurality of new engine characteristic data under all atmospheric temperature conditions; s3, forming a first relation curve between the atmospheric temperature and the low-pressure physical rotating speed; s4, forming a second relation curve between the atmospheric temperature and the exhaust temperature; s5, if the engine is in a temperature limiting state, determining a first relation curve through the atmospheric temperature and the low-pressure physical rotating speed, and if the engine is in a rotation limiting state, determining a second relation curve through the atmospheric temperature and the exhaust temperature; and S6, determining corresponding key parameters. The application improves the accuracy of the engine performance attenuation assessment and ensures the safety of the engine in the use process.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to a method and a device for determining performance attenuation parameters of a turbofan engine.
Background
The aeroengine performance degradation refers to a situation in which the thrust force decreases and the exhaust temperature increases with an increase in operating time based on the engine factory acceptance performance. Performance degradation is a critical issue encountered in aeroengine use, resulting in numerous engine performance degradation factors, including design, materials, manufacture, and use, being an integral feature of the industry.
During the use process, the performance attenuation of the engine can lead to the reduction of thrust and the increase of fuel consumption rate, and the use of the engine is seriously influenced, so that the assessment of the performance attenuation of the engine is very important. Currently, residential engines typically choose an engine exhaust temperature margin as an indicator for assessing engine performance degradation.
The engine exhaust temperature margin is used as a performance decay index for evaluating the engine, and although the engine is visual, the engine cannot work at the standard atmospheric temperature; at different atmospheric temperatures, the engine cannot be strictly maintained due to geometric similarity, the engine characteristics are offset, the converted exhaust temperature is also changed, and larger errors can be generated on the accuracy of evaluating the engine performance.
Disclosure of Invention
In order to solve one of the problems, the application provides a method and a device for determining performance attenuation parameters of a turbofan engine, which ensure that the performance parameters of the engine working at different atmospheric temperatures can be converted to the same standard for performance attenuation assessment, and improve the accuracy of the performance attenuation assessment of the engine.
The first aspect of the present application provides a method for determining performance attenuation parameters of a turbofan engine, comprising:
Step S1, acquiring a plurality of engine characteristic data under different atmospheric temperature conditions, wherein each engine characteristic data corresponds to one atmospheric temperature condition and comprises a corresponding atmospheric temperature, a low-pressure physical rotating speed of an engine and an exhaust temperature;
s2, regarding any one atmospheric temperature, taking the corresponding exhaust temperature as a limit value, when the selected atmospheric temperature is more than or equal to 15 ℃, improving the control rule of the low-pressure physical rotating speed by 10%, and under the condition of the limit value, acquiring a plurality of new engine characteristic data under all atmospheric temperature conditions;
S3, forming a plurality of new engine characteristic data corresponding to each limiting value into a first relation curve between the atmospheric temperature and the low-pressure physical rotating speed, wherein each first relation curve corresponding to each limiting value represents key parameters of engine performance attenuation, and the key parameters corresponding to each first relation curve from top to bottom are in a decreasing trend;
S4, forming a plurality of new engine characteristic data corresponding to each limiting value into a second relation curve between the atmospheric temperature and the exhaust temperature, wherein key parameters of the second relation curves corresponding to the limiting values from left to right are the same as key parameters corresponding to the first relation curves from top to bottom;
S5, determining a limiting state of the engine, determining a corresponding first relation curve through the actually measured atmospheric temperature and the low-pressure physical rotation speed if the engine is in the temperature limiting state, and determining a corresponding second relation curve through the actually measured atmospheric temperature and the exhaust temperature if the engine is in the rotation limiting state;
And S6, determining corresponding key parameters based on the first relation curve or the second relation curve, wherein the larger the key parameters are, the smaller the engine performance attenuation is, and otherwise, the smaller the key parameters are, the larger the engine performance attenuation is.
Preferably, in step S1, engine characteristic data for each atmospheric temperature condition is determined by an engine simulation calculation model.
Preferably, in step S5, the corresponding first or second relationship is determined by linear interpolation.
Preferably, the method further comprises the step of setting a key parameter threshold, and if the key parameter corresponding to the determined first relation curve or second relation curve is smaller than the key parameter threshold, determining that the engine needs to be returned to a factory for repair.
In a second aspect, the present application provides an apparatus for determining performance decay parameters of a turbofan engine, comprising:
The engine characteristic data acquisition module is used for acquiring a plurality of engine characteristic data under different atmospheric temperature conditions, wherein each engine characteristic data corresponds to one atmospheric temperature condition and comprises the corresponding atmospheric temperature, the low-pressure physical rotating speed of the engine and the exhaust temperature;
The limiting value determining module is used for regarding any one atmospheric temperature as a limiting value, when the selected atmospheric temperature is more than or equal to 15 ℃, the control rule of the low-pressure physical rotating speed is improved by 10%, and under the condition of the limiting value, a plurality of new engine characteristic data under all atmospheric temperature conditions are obtained;
the first relation curve determining module is used for forming a plurality of new engine characteristic data corresponding to each limiting value into a first relation curve between the atmospheric temperature and the low-pressure physical rotating speed, wherein each first relation curve corresponding to each limiting value represents a key parameter of engine performance attenuation, and the key parameters corresponding to each first relation curve from top to bottom are in a decreasing trend;
the second relation curve determining module is used for forming a plurality of new engine characteristic data corresponding to each limiting value into a second relation curve between the atmospheric temperature and the exhaust temperature, and key parameters of the second relation curves corresponding to the limiting values from left to right are the same as key parameters corresponding to the first relation curves from top to bottom;
The engine test data processing module is used for determining a limiting state of the engine, determining a corresponding first relation curve through the actually measured atmospheric temperature and the low-pressure physical rotating speed if the engine is in the limiting state, and determining a corresponding second relation curve through the actually measured atmospheric temperature and the exhaust temperature if the engine is in the limiting state;
And the performance attenuation determining module is used for determining corresponding key parameters based on the first relation curve or the second relation curve, wherein the larger the key parameters are, the smaller the engine performance attenuation is, and otherwise, the smaller the key parameters are, the larger the engine performance attenuation is.
Preferably, in the engine characteristic data acquisition module, engine characteristic data under each atmospheric temperature condition is determined by an engine simulation calculation model.
Preferably, the engine test data processing module includes an interpolation calculation unit for determining the corresponding first or second relationship by linear interpolation.
Preferably, the device for determining the performance attenuation parameter of the turbofan engine further comprises an alarm module, wherein the alarm module is used for setting a key parameter threshold value, and if the key parameter corresponding to the determined first relation curve or second relation curve is smaller than the key parameter threshold value, the engine is determined to need to be returned to a factory for repair.
The application improves the accuracy of the engine performance attenuation assessment and ensures the safety of the engine in the use process.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of a method of determining turbofan engine performance degradation parameters in accordance with the present application.
Fig. 2 is a schematic diagram of a first relationship.
Fig. 3 is a schematic diagram of a second relationship.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present application without making any inventive effort, are intended to fall within the scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In a first aspect, the present application provides a method for determining performance attenuation parameters of a turbofan engine, as shown in fig. 1, mainly including:
Step S1, acquiring a plurality of engine characteristic data under different atmospheric temperature conditions, wherein each engine characteristic data corresponds to one atmospheric temperature condition and comprises the corresponding atmospheric temperature, the low-pressure physical rotating speed of the engine and the exhaust temperature.
In some alternative embodiments, in step S1, engine characteristic data for each atmospheric temperature condition is determined by an engine simulation calculation model.
In the embodiment, the temperature characteristic curves under different atmospheric temperature conditions (T 11、T12、T13～T1n) are calculated through an engine simulation calculation model to obtain key characteristic parameters of the engine, namely an air inlet temperature T 1, a low-pressure physical rotating speed n 1, an exhaust temperature T 6.[(T11、n11, T 61)、(T12、n12, T 62)～(T1n、n1n and T 6n under each corresponding atmospheric temperature condition
And S2, regarding any atmospheric temperature, taking the corresponding exhaust temperature as a limit value, when the selected atmospheric temperature is more than or equal to 15 ℃, improving the control rule of the low-pressure physical rotating speed by 10%, and acquiring a plurality of new engine characteristic data under all atmospheric temperature conditions under the condition of the limit value.
Specifically, first, an atmospheric temperature T 1k is selected from the engine characteristic data [ (T 11、n11 and T 61)、(T12、n12 and T 62)～(T1n、n1n and T 6n) ] obtained in step S1; secondly, adjusting the engine exhaust temperature limit value in the calculation model to an exhaust temperature T 6k corresponding to the atmospheric temperature T 1k; meanwhile, if T 1k is more than or equal to 15 ℃, the control law of the low-voltage physical rotating speed n 1 is improved by 10%; then, calculating temperature characteristic curves under different atmospheric temperature conditions (T 11、T12、T13～T1n) to obtain engine characteristic data [ (T 11、n1k1 and T 6k1)、(T1k2、n1k2 and T 6k2)～(T1n、n1kn and T 6kn) ] of the current atmospheric temperature limit state; and finally repeating the steps, and selecting the rest atmospheric temperature from the engine characteristic data obtained in the step S1 to obtain the engine characteristic data in different atmospheric temperature limiting states.
And S3, forming a plurality of new engine characteristic data corresponding to each limiting value into a first relation curve between the atmospheric temperature and the low-pressure physical rotating speed, wherein the first relation curves corresponding to the limiting values represent key parameters of engine performance attenuation, and the key parameters corresponding to the first relation curves from top to bottom are in a decreasing trend.
As shown in fig. 2, according to the engine characteristic data of different temperature limit states of the atmosphere obtained in the step S2, a T 1～n1 curve is drawn, wherein n 1RX is characterized as an engine performance attenuation key parameter, and values k 1-k 10 of n 1RX are intersections of the corresponding curves and the temperature 15 ℃ (dotted lines in the figure); referring to fig. 2, the key parameter k1 is assigned by using the value of n1 corresponding to the highest point of the first relation curve, and the key parameter from top to bottom is smaller and smaller, wherein for k5, k6 and k7, since the curve corresponding to k7 falls back earlier relative to the curve corresponding to k6, the value of k7 is smaller than the value of k6, the corresponding value of k6 is smaller than the value of k5, and in sum, the key parameter k1 is largest, k10 is smallest, for example, k1 is 102%, k2 is 101.5%, and k10 is 96%.
And S4, forming a second relation curve between the atmospheric temperature and the exhaust temperature by using a plurality of new engine characteristic data corresponding to each limiting value, wherein key parameters of the second relation curves corresponding to the limiting values from left to right are the same as key parameters corresponding to the first relation curves from top to bottom.
As shown in fig. 3, according to the engine characteristic data of different atmospheric temperature limit states obtained in step S2, curves T1 to T6 are drawn, where n 1RX is characterized as an engine performance attenuation key parameter, and the values of the parameters are given in fig. 2 in a one-to-one correspondence.
And S5, determining a limiting state of the engine, determining a corresponding first relation curve through the actually measured atmospheric temperature and the low-pressure physical rotating speed if the engine is in the temperature limiting state, and determining a corresponding second relation curve through the actually measured atmospheric temperature and the exhaust temperature if the engine is in the rotation limiting state.
In some alternative embodiments, in step S5, the corresponding first or second relationship is determined by linear interpolation.
The engine test is performed by first identifying the engine limit state. When the engine is in a temperature limited state, n 1RX,n1RX is determined by measured T 1/n1 according to FIG. 2, and can be determined by linear interpolation of each curve in the graph and its identified n 1RX. When the engine is in a limited rotation state, n 1RX,n1RX is determined by actually measured T 1/T6 according to FIG. 3, and can be determined by linear interpolation of each curve and the n 1RX identified by each curve in the graph.
And S6, determining corresponding key parameters based on the first relation curve or the second relation curve, wherein the larger the key parameters are, the smaller the engine performance attenuation is, and otherwise, the smaller the key parameters are, the larger the engine performance attenuation is.
In the embodiment, the obtained n 1RX is the engine performance attenuation parameter, and the larger n 1RX is, the smaller the engine performance attenuation is, the larger the thrust is, and the lower the fuel consumption is; conversely, a smaller n 1RX represents a larger engine performance decay, a smaller thrust force and a higher fuel consumption rate.
In some optional embodiments, setting a critical parameter threshold, that is, a red line value, and if the determined critical parameter corresponding to the first relationship curve or the second relationship curve is smaller than the critical parameter threshold, determining that the engine needs to be returned to the factory for repair.
The application improves the accuracy of the engine performance attenuation assessment and ensures the safety of the engine in the use process.
In a second aspect, the present application provides an apparatus for determining performance decay parameters of a turbofan engine, comprising:
The engine characteristic data acquisition module is used for acquiring a plurality of engine characteristic data under different atmospheric temperature conditions, wherein each engine characteristic data corresponds to one atmospheric temperature condition and comprises the corresponding atmospheric temperature, the low-pressure physical rotating speed of the engine and the exhaust temperature;
The limiting value determining module is used for regarding any one atmospheric temperature as a limiting value, when the selected atmospheric temperature is more than or equal to 15 ℃, the control rule of the low-pressure physical rotating speed is improved by 10%, and under the condition of the limiting value, a plurality of new engine characteristic data under all atmospheric temperature conditions are obtained;
the first relation curve determining module is used for forming a plurality of new engine characteristic data corresponding to each limiting value into a first relation curve between the atmospheric temperature and the low-pressure physical rotating speed, wherein each first relation curve corresponding to each limiting value represents a key parameter of engine performance attenuation, and the key parameters corresponding to each first relation curve from top to bottom are in a decreasing trend;
the second relation curve determining module is used for forming a plurality of new engine characteristic data corresponding to each limiting value into a second relation curve between the atmospheric temperature and the exhaust temperature, and key parameters of the second relation curves corresponding to the limiting values from left to right are the same as key parameters corresponding to the first relation curves from top to bottom;
The engine test data processing module is used for determining a limiting state of the engine, determining a corresponding first relation curve through the actually measured atmospheric temperature and the low-pressure physical rotating speed if the engine is in the limiting state, and determining a corresponding second relation curve through the actually measured atmospheric temperature and the exhaust temperature if the engine is in the limiting state;
And the performance attenuation determining module is used for determining corresponding key parameters based on the first relation curve or the second relation curve, wherein the larger the key parameters are, the smaller the engine performance attenuation is, and otherwise, the smaller the key parameters are, the larger the engine performance attenuation is.
In some alternative embodiments, in the engine characteristic data acquisition module, engine characteristic data under each atmospheric temperature condition is determined by an engine simulation calculation model.
In some alternative embodiments, the engine test data processing module includes an interpolation calculation unit for determining the corresponding first or second relationship by linear interpolation.
In some optional embodiments, the device for determining the performance attenuation parameter of the turbofan engine further includes an alarm module, configured to set a key parameter threshold, and if the key parameter corresponding to the determined first relationship curve or the determined second relationship curve is smaller than the key parameter threshold, determine that the engine needs to be returned to the factory for repair.
While the application has been described in detail in the foregoing general description and with reference to specific embodiments thereof, it will be apparent to one skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the application and are intended to be within the scope of the application as claimed.
Claims (8)
1. A method of determining a turbofan engine performance degradation parameter, comprising:
Step S1, acquiring a plurality of engine characteristic data under different atmospheric temperature conditions, wherein each engine characteristic data corresponds to one atmospheric temperature condition and comprises a corresponding atmospheric temperature, a low-pressure physical rotating speed of an engine and an exhaust temperature;
s2, regarding any one atmospheric temperature, taking the corresponding exhaust temperature as a limit value, when the selected atmospheric temperature is more than or equal to 15 ℃, improving the control rule of the low-pressure physical rotating speed by 10%, and under the condition of the limit value, acquiring a plurality of new engine characteristic data under all atmospheric temperature conditions;
S3, forming a plurality of new engine characteristic data corresponding to each limiting value into a first relation curve between the atmospheric temperature and the low-pressure physical rotating speed, wherein each first relation curve corresponding to each limiting value represents key parameters of engine performance attenuation, and the key parameters corresponding to each first relation curve from top to bottom are in a decreasing trend;
S4, forming a plurality of new engine characteristic data corresponding to each limiting value into a second relation curve between the atmospheric temperature and the exhaust temperature, wherein key parameters of the second relation curves corresponding to the limiting values from left to right are the same as key parameters corresponding to the first relation curves from top to bottom;
S5, determining a limiting state of the engine, determining a corresponding first relation curve through the actually measured atmospheric temperature and the low-pressure physical rotation speed if the engine is in the temperature limiting state, and determining a corresponding second relation curve through the actually measured atmospheric temperature and the exhaust temperature if the engine is in the rotation limiting state;
And S6, determining corresponding key parameters based on the first relation curve or the second relation curve, wherein the larger the key parameters are, the smaller the engine performance attenuation is, and otherwise, the smaller the key parameters are, the larger the engine performance attenuation is.
2. The method for determining a turbofan engine performance degradation parameter of claim 1, wherein in step S1, engine characteristic data for each atmospheric temperature condition is determined by an engine simulation calculation model.
3. The method for determining a turbofan engine performance degradation parameter of claim 1, wherein in step S5, the corresponding first or second relationship is determined by linear interpolation.
4. The method of determining a turbofan engine performance degradation parameter of claim 1, further comprising setting a key parameter threshold, and if the key parameter corresponding to the determined first or second relationship is less than the key parameter threshold, determining that the engine requires a return to service repair.
5. An apparatus for determining a turbofan engine performance degradation parameter, comprising:
The engine characteristic data acquisition module is used for acquiring a plurality of engine characteristic data under different atmospheric temperature conditions, wherein each engine characteristic data corresponds to one atmospheric temperature condition and comprises the corresponding atmospheric temperature, the low-pressure physical rotating speed of the engine and the exhaust temperature;
The limiting value determining module is used for regarding any one atmospheric temperature as a limiting value, when the selected atmospheric temperature is more than or equal to 15 ℃, the control rule of the low-pressure physical rotating speed is improved by 10%, and under the condition of the limiting value, a plurality of new engine characteristic data under all atmospheric temperature conditions are obtained;
the first relation curve determining module is used for forming a plurality of new engine characteristic data corresponding to each limiting value into a first relation curve between the atmospheric temperature and the low-pressure physical rotating speed, wherein each first relation curve corresponding to each limiting value represents a key parameter of engine performance attenuation, and the key parameters corresponding to each first relation curve from top to bottom are in a decreasing trend;
the second relation curve determining module is used for forming a plurality of new engine characteristic data corresponding to each limiting value into a second relation curve between the atmospheric temperature and the exhaust temperature, and key parameters of the second relation curves corresponding to the limiting values from left to right are the same as key parameters corresponding to the first relation curves from top to bottom;
The engine test data processing module is used for determining a limiting state of the engine, determining a corresponding first relation curve through the actually measured atmospheric temperature and the low-pressure physical rotating speed if the engine is in the limiting state, and determining a corresponding second relation curve through the actually measured atmospheric temperature and the exhaust temperature if the engine is in the limiting state;
And the performance attenuation determining module is used for determining corresponding key parameters based on the first relation curve or the second relation curve, wherein the larger the key parameters are, the smaller the engine performance attenuation is, and otherwise, the smaller the key parameters are, the larger the engine performance attenuation is.
6. The apparatus for determining a turbofan engine performance degradation parameter of claim 5, wherein in said engine signature data acquisition module, engine signature data for each atmospheric temperature condition is determined by an engine simulation calculation model.
7. The apparatus for determining a turbofan engine performance degradation parameter of claim 5, wherein the engine test data processing module comprises an interpolation calculation unit for determining the corresponding first or second relationship by linear interpolation.
8. The turbofan engine performance degradation parameter determination apparatus of claim 5, further comprising an alert module configured to set a key parameter threshold, and determine that the engine requires a return to service repair if the key parameter corresponding to the determined first or second relationship is less than the key parameter threshold.
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| CN111175054A (en) * | 2020-01-08 | 2020-05-19 | 沈阳航空航天大学 | Aeroengine fault diagnosis method based on data driving |
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| JP4179192B2 (en) * | 2004-03-08 | 2008-11-12 | 株式会社デンソー | Combustion state detection device for internal combustion engine |
| CN114112416B (en) * | 2021-11-24 | 2023-05-05 | 中国航发沈阳发动机研究所 | Turbofan engine bench performance parameter correction benchmark determination method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108106849A (en) * | 2017-12-14 | 2018-06-01 | 中国航发沈阳发动机研究所 | A kind of fanjet component feature parameter identification method |
| CN111175054A (en) * | 2020-01-08 | 2020-05-19 | 沈阳航空航天大学 | Aeroengine fault diagnosis method based on data driving |
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