CN114544180A - Engine large throttle evaluation method and device - Google Patents
Engine large throttle evaluation method and device Download PDFInfo
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- CN114544180A CN114544180A CN202111641081.XA CN202111641081A CN114544180A CN 114544180 A CN114544180 A CN 114544180A CN 202111641081 A CN202111641081 A CN 202111641081A CN 114544180 A CN114544180 A CN 114544180A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The application belongs to the field of engine design, and particularly relates to an engine throttle assessment method and device. The method comprises the steps of S1, obtaining a plurality of discrete point coordinates formed by each time point and a thrust ratio parameter under the time point, wherein the thrust ratio parameter is the ratio of thrust corresponding to each time point to intermediate thrust of the engine given based on the large throttle thrust characteristic of the engine; step S2, connecting the discrete points according to time sequence to form a plurality of line segments, and taking the slope of each line segment as a reference slope; step S3, acquiring the engine thrust of each time point in the process of large throttle acceleration of the engine, and calculating the actual ratio of the engine thrust of each time point to the intermediate thrust; step S4, determining a plurality of slopes as actual slopes according to the actual ratios of adjacent time points; and step S5, evaluating the throttle valve characteristic of the engine according to the actual slope and the reference slope. The method is more accurate and effective in evaluating the acceleration characteristic of the large throttle of a new research and development motivation.
Description
Technical Field
The application belongs to the field of engine design, and particularly relates to an engine throttle assessment method and device.
Background
The large throttle characteristic of a conventional carrier-based aircraft engine is characterized by describing the acceleration characteristic of the engine by testing a curve of thrust and time, generally specifying the relationship between the time and the thrust for pushing the throttle from an engine throttling state to an intermediate state, checking the large throttle characteristic of each engine before the engine leaves a factory, and leaving the factory only when the characteristic is not lower than the characteristic in the curve, wherein a schematic diagram is shown in fig. 1. The conventional engine acceleration evaluation means above mainly evaluates the large and small throttle characteristics by a fixed time limit. The essence of the acceleration and deceleration characteristics of the engine is the slope of the curve of thrust and time, that is, the larger the slope, the steeper the curve, the better the acceleration and deceleration performance, the smaller the slope, the gentler the curve, and the worse the acceleration and deceleration performance. Meanwhile, the curves of each type of engine are different, and transverse comparison cannot be achieved.
Disclosure of Invention
In order to solve the problems, the application provides an engine throttle valve evaluation method and device, namely a method for evaluating a carrier-based aircraft engine by using a slope of thrust changing along with time, and simultaneously, the acceleration performances of different engines are transversely compared in a thrust percentage mode by unifying standards.
The application provides an engine large throttle evaluation method in a first aspect, which mainly comprises the following steps:
step S1, obtaining a plurality of discrete point coordinates formed by each time point and a thrust ratio parameter under the time point, wherein the thrust ratio parameter is a ratio of thrust corresponding to each time point to engine intermediate thrust given based on the thrust characteristic of the engine large throttle;
step S2, connecting the discrete points according to time sequence to form a plurality of line segments, and taking the slope of each line segment as a reference slope;
step S3, acquiring the engine thrust of each time point in the process of large throttle acceleration of the engine, and calculating the actual ratio of the engine thrust of each time point to the intermediate thrust;
step S4, determining a plurality of slopes as actual slopes according to the actual ratios of adjacent time points;
and step S5, evaluating the characteristics of the engine throttle valve according to the actual slope and the reference slope.
Preferably, in step S1, the number of the discrete point coordinates is at least 10.
Preferably, step S2 is followed by further evaluating the large throttle characteristics of different engines according to the reference slope.
Preferably, in step S5, the evaluating the engine large throttle characteristic includes:
determining the number of actual slopes greater than reference slopes in the acceleration process of the large throttle;
and if the number accounts for 80% of all reference slope numbers, the large throttle acceleration performance of the engine is considered to meet the design requirement.
The second aspect of the present application provides an engine throttle evaluation device, which mainly includes:
the coordinate point acquisition module is used for acquiring a plurality of discrete point coordinates consisting of each time point and a thrust ratio parameter under the time point, wherein the thrust ratio parameter is a ratio of thrust corresponding to each time point to intermediate thrust of the engine, which is given based on the thrust characteristics of a large throttle of the engine;
the reference slope calculation module is used for connecting the discrete points in time sequence to form a plurality of line segments, and the slope of each line segment is used as the reference slope;
the engine state acquisition module is used for acquiring the engine thrust of each time point in the process of large throttle acceleration of the engine and calculating the actual ratio of the engine thrust of each time point to the intermediate thrust;
the actual slope calculation module is used for determining a plurality of slopes as actual slopes according to the actual ratios of adjacent time points;
and the engine throttle characteristic evaluation module is used for evaluating the engine throttle characteristic according to the actual slope and the reference slope.
Preferably, in the coordinate point obtaining module, the number of the discrete point coordinates is at least 10.
Preferably, the engine large throttle evaluation device further includes:
and the transverse evaluation module is used for transversely evaluating the large throttle characteristics of different engines according to the reference slope.
Preferably, the engine wide-throttle characteristic evaluation module includes:
the comparison unit is used for determining the number of actual slopes greater than reference slopes in the acceleration process of the throttle valve;
and the evaluation unit is used for considering that the large throttle acceleration performance of the engine meets the design requirement when the quantity accounts for 80% of all reference slope quantities.
The method and the device can be used for evaluating the large throttle of a newly researched and developed engine, unify the thrust ratio standard and enable the large throttle characteristics of different engines to be transversely compared. Therefore, the method is more objective and effective in restricting the characteristics of the engine and the throttle of the carrier-based aircraft and has wider application.
Drawings
Fig. 1 is a schematic diagram of a conventional engine large throttle characteristic curve.
FIG. 2 is a flow chart of a preferred embodiment of the engine throttle gain evaluation method of the present application.
FIG. 3 is a schematic diagram of a large throttle characteristic curve according to the embodiment of the present application shown in FIG. 2.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, 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. 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 present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The present application provides, in a first aspect, an engine large throttle evaluation method, as shown in fig. 2, which mainly includes:
step S1, obtaining a plurality of discrete point coordinates formed by each time point and a thrust ratio parameter under the time point, wherein the thrust ratio parameter is a ratio of thrust corresponding to each time point to engine intermediate thrust given based on the thrust characteristic of the engine large throttle;
step S2, connecting the discrete points according to time sequence to form a plurality of line segments, and taking the slope of each line segment as a reference slope;
step S3, acquiring the engine thrust of each time point in the process of large throttle acceleration of the engine, and calculating the actual ratio of the engine thrust of each time point to the intermediate thrust;
step S4, determining a plurality of slopes as actual slopes according to the actual ratios of adjacent time points;
and step S5, evaluating the characteristics of the engine throttle valve according to the actual slope and the reference slope.
According to the method and the device, a new large throttle evaluation method based on the slope can be formed based on the existing large throttle evaluation characteristic of the engine, so that the large throttle acceleration characteristic evaluation of a new research and development motivation is more accurate and effective.
In some alternative embodiments, in step S1, the number of discrete point coordinates is at least 10.
In some alternative embodiments, step S2 is followed by further comprising laterally evaluating large throttle characteristics of different engines according to a reference slope.
In some alternative embodiments, evaluating the engine wide throttle characteristic comprises:
determining the number of actual slopes greater than reference slopes in the acceleration process of the large throttle;
and if the number accounts for 80% of all reference slope numbers, the large throttle acceleration performance of the engine is considered to meet the design requirement.
The thrust and the thrust of intermediate state are used as the ordinate to this application, can accomplish standard normalization like this, and the big throttle characteristic curve of all engines can transversely contrast promptly. The slope of each of the small curves (K1, K2, K3, Kn) is then used as an evaluation to constrain the behavior of the engine's large throttle. An example is shown in figure 3.
The novel assessment method for the large throttle of the ship-based aircraft engine reflects the acceleration essence more objectively: the slope rate, simultaneously, unified the thrust ratio standard, the big throttle characteristic that lets different engines can transversely compare. Therefore, the method is more objective and effective in restricting the characteristics of the large and small throttles of the engine of the carrier-based aircraft, and is more widely applied.
The second aspect of the present application provides an engine large throttle evaluation device corresponding to the above method, which mainly includes:
the coordinate point acquisition module is used for acquiring a plurality of discrete point coordinates consisting of each time point and a thrust ratio parameter under the time point, wherein the thrust ratio parameter is a ratio of thrust corresponding to each time point to intermediate thrust of the engine, which is given based on the thrust characteristic of the large throttle of the engine;
the reference slope calculation module is used for connecting the discrete points in time sequence to form a plurality of line segments, and the slope of each line segment is used as the reference slope;
the engine state acquisition module is used for acquiring the engine thrust of each time point in the process of large throttle acceleration of the engine and calculating the actual ratio of the engine thrust of each time point to the intermediate thrust;
the actual slope calculation module is used for determining a plurality of slopes as actual slopes according to the actual ratios of adjacent time points;
and the engine throttle characteristic evaluation module is used for evaluating the engine throttle characteristic according to the actual slope and the reference slope.
In some optional embodiments, in the coordinate point obtaining module, the number of the discrete point coordinates is at least 10.
In some alternative embodiments, the engine large throttle evaluation device further comprises:
and the transverse evaluation module is used for transversely evaluating the large throttle characteristics of different engines according to the reference slope.
In some alternative embodiments, the engine throttle characteristic evaluation module comprises:
the comparison unit is used for determining the number of actual slopes greater than reference slopes in the acceleration process of the throttle valve;
and the evaluation unit is used for considering that the large throttle acceleration performance of the engine meets the design requirement when the quantity accounts for 80% of all reference slope quantities.
Although the present application has been described in detail with respect to the general description and specific embodiments, it will be apparent to those skilled in the art that certain modifications or improvements may be made based on the present application. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.
Claims (8)
1. An engine large throttle evaluation method, comprising:
step S1, obtaining a plurality of discrete point coordinates formed by each time point and a thrust ratio parameter under the time point, wherein the thrust ratio parameter is a ratio of thrust corresponding to each time point and engine intermediate thrust given on the basis of the large throttle thrust characteristic of the engine;
step S2, connecting the discrete points according to time sequence to form a plurality of line segments, and taking the slope of each line segment as a reference slope;
step S3, acquiring the engine thrust of each time point in the process of large throttle acceleration of the engine, and calculating the actual ratio of the engine thrust of each time point to the intermediate thrust;
step S4, determining a plurality of slopes as actual slopes according to the actual ratios of adjacent time points;
and step S5, evaluating the characteristics of the engine throttle valve according to the actual slope and the reference slope.
2. The engine throttle macrospeed evaluation method of claim 1, characterized in that in step S1, the number of the discrete point coordinates is at least 10.
3. The engine wide throttle estimation method of claim 1, characterized in that step S2 is followed by further comprising estimating wide throttle characteristics of different engines laterally according to a reference slope.
4. The engine throttle valve estimation method of claim 1, wherein in step S5, estimating the engine throttle valve characteristic comprises:
determining the number of actual slopes greater than reference slopes in the acceleration process of the large throttle;
and if the number accounts for 80% of all reference slope numbers, the large throttle acceleration performance of the engine is considered to meet the design requirement.
5. An engine large throttle evaluation device, comprising:
the coordinate point acquisition module is used for acquiring a plurality of discrete point coordinates consisting of each time point and a thrust ratio parameter under the time point, wherein the thrust ratio parameter is a ratio of thrust corresponding to each time point to intermediate thrust of the engine, which is given based on the thrust characteristics of a large throttle of the engine;
the reference slope calculation module is used for connecting the discrete points in time sequence to form a plurality of line segments, and the slope of each line segment is used as the reference slope;
the engine state acquisition module is used for acquiring the engine thrust of each time point in the process of large throttle acceleration of the engine and calculating the actual ratio of the engine thrust of each time point to the intermediate thrust;
the actual slope calculation module is used for determining a plurality of slopes as actual slopes according to the actual ratios of adjacent time points;
and the engine throttle characteristic evaluation module is used for evaluating the engine throttle characteristic according to the actual slope and the reference slope.
6. The engine throttle cruiser evaluation device of claim 5, wherein the number of discrete point coordinates in the coordinate point acquisition module is at least 10.
7. The engine wide throttle evaluation device of claim 5, further comprising:
and the transverse evaluation module is used for transversely evaluating the large throttle characteristics of different engines according to the reference slope.
8. The engine throttle override apparatus according to claim 5, wherein the engine throttle characteristic evaluation module includes:
the comparison unit is used for determining the number of actual slopes greater than reference slopes in the acceleration process of the throttle valve;
and the evaluation unit is used for considering that the large throttle acceleration performance of the engine meets the design requirement when the quantity accounts for 80% of all reference slope quantities.
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| US4003249A (en) * | 1975-12-29 | 1977-01-18 | The Boeing Company | Thrust correlated engine pressure ratio indicator and method for turbofan engines with mixer-type nozzles |
| EP1705355A1 (en) * | 2005-03-25 | 2006-09-27 | Delphi Technologies, Inc. | Method for determining operating parameters of an injection system |
| KR101340449B1 (en) * | 2012-12-13 | 2013-12-11 | 현대중공업 주식회사 | Estimation method of steady state reaching time |
| CN104359678A (en) * | 2014-11-10 | 2015-02-18 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for automatically judging thrust transient of aeroengine |
| CA2870512A1 (en) * | 2013-11-12 | 2015-05-12 | Aero Systems Engineering, Inc. | Systems and methods for improved accuracy |
| US20180320599A1 (en) * | 2017-05-03 | 2018-11-08 | Pratt & Whitney Canada Corp. | Detection of uncommanded and uncontrollable high thrust events |
| CN112417595A (en) * | 2020-11-19 | 2021-02-26 | 中国航发沈阳发动机研究所 | Method for evaluating installation thrust of aircraft engine |
-
2021
- 2021-12-29 CN CN202111641081.XA patent/CN114544180A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4003249A (en) * | 1975-12-29 | 1977-01-18 | The Boeing Company | Thrust correlated engine pressure ratio indicator and method for turbofan engines with mixer-type nozzles |
| EP1705355A1 (en) * | 2005-03-25 | 2006-09-27 | Delphi Technologies, Inc. | Method for determining operating parameters of an injection system |
| KR101340449B1 (en) * | 2012-12-13 | 2013-12-11 | 현대중공업 주식회사 | Estimation method of steady state reaching time |
| CA2870512A1 (en) * | 2013-11-12 | 2015-05-12 | Aero Systems Engineering, Inc. | Systems and methods for improved accuracy |
| CN104359678A (en) * | 2014-11-10 | 2015-02-18 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for automatically judging thrust transient of aeroengine |
| US20180320599A1 (en) * | 2017-05-03 | 2018-11-08 | Pratt & Whitney Canada Corp. | Detection of uncommanded and uncontrollable high thrust events |
| CN112417595A (en) * | 2020-11-19 | 2021-02-26 | 中国航发沈阳发动机研究所 | Method for evaluating installation thrust of aircraft engine |
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