CN104359678A - Method for automatically judging thrust transient of aeroengine - Google Patents
Method for automatically judging thrust transient of aeroengine Download PDFInfo
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- CN104359678A CN104359678A CN201410628140.3A CN201410628140A CN104359678A CN 104359678 A CN104359678 A CN 104359678A CN 201410628140 A CN201410628140 A CN 201410628140A CN 104359678 A CN104359678 A CN 104359678A
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Abstract
The invention relates to a method for automatically judging thrust transient of an aeroengine. The method includes applying a parameter data oscilloscope function of a test bench data collecting system to take a standard thrust transient response acceptance graph of the aeroengine as a standard curve to be input into a computer; performing a thrust transient experiment on the aeroengine, and moving a throttle lever; when moving time of the throttle lever meets the requirements, drawing an actual thrust transient response curve of the aeroengine in the standard thrust transient response acceptance graph of the aeroengine, and acquiring an automatic interpreting curve graph of the actual thrust transient response curve of the aeroengine and the standard curve; comparing actual thrust with standard thrust at a same moment in the above relation graph; when the actual thrust is larger than or equal to the standard thrust, giving out a conclusion with qualified thrust in the automatic interpreting curve graph. By the method, thrust dynamic response characteristics of the aeroengine are automatically evaluated in real time, manpower and time are saved, in-plant test run number and running time of the aeroengine are reduced, and production and repair cost of the aeroengine is reduced.
Description
Technical field
The present invention relates to a kind of aeroengine thrust decision technology, specifically a kind of aeroengine thrust transition automatic judging method.
Background technology
Certain model aeromotor requires higher to thrust transient characteristic, needs the special project test carrying out motor power dynamic response characteristic, by thrust response curve evaluation motor power transient performance in test.All the data according to test bay data acquisition system (DAS) record in the past, artificial reading Thrust Level Angel, the parameter such as thrust and time, first judge whether the time of throttle lever change conforms with the regulations, then the Plotting data conformed with the regulations by throttle lever traveling time to normal rated thrust response examination figure (Fig. 1) obtains the graph of a relation (Fig. 2) of engine actual thrust transition curve and normal rated thrust transition curve, by artificial contrast's engine actual thrust response curve and examination curve, provide engine actual thrust transition evaluation result, owing to can only judge to adjust again by Man Graphics afterwards, often need the process repeatedly testing-draw judgement-adjustment several times, waste time and energy, add every cost.At present, the method can carrying out real-time automatic evaluation thrust transient characteristic is not also had.
Summary of the invention
Judgement for aeroengine thrust in prior art is drawn thrust characteristic by artificial described point, can not be evaluated in real time, the problems such as high wasted by manpower and time cost, and the technical problem to be solved in the present invention is to provide a kind of aeroengine thrust transition automatic judging method that can realize the thrust dynamic response characteristic of real-time automatic evaluation engine.
For solving the problems of the technologies described above, the technical solution used in the present invention is:
A kind of aeroengine thrust transition of the present invention automatic judging method comprises the following steps:
The parameter oscillography function of application test bay data acquisition system (DAS), checks and accepts figure as typical curve input computer using the normal rated thrust transient response of aeromotor;
Thrust transient test is carried out to aeromotor, mobile throttle lever;
When throttle lever traveling time conforms with the regulations, the actual thrust transient response curve of aeromotor is plotted in the normal rated thrust transient response examination figure of aeromotor, obtains the automatic interpretation curve map of aeromotor actual thrust response transition curve and typical curve;
The size of synchronization actual thrust and normal rated thrust is contrasted in above-mentioned relation figure;
When actual thrust is more than or equal to normal rated thrust, in automatic interpretation curve map, provide the conclusion that thrust is qualified.
When actual thrust is less than normal rated thrust, in automatic interpretation curve map, provide the underproof conclusion of thrust.
If throttle lever traveling time is against regulation, then do not draw actual thrust transient response curve.
The present invention has following beneficial effect and advantage:
1. apply the thrust dynamic response characteristic that the inventive method can realize real-time automatic evaluation engine, save manpower and time, reduce test run number of times and the duration of runs in engine works, reduce engine production repair cost.
Accompanying drawing explanation
Fig. 1 is normal rated thrust transient response examination figure;
Fig. 2 is the artificial Detection curve schematic diagram drawn in prior art;
Fig. 3 is the inventive method process flow diagram;
Fig. 4 is engine actual thrust transient response curve
Fig. 5 is automatic interpretation curve map schematic diagram in the present invention.
Embodiment
Below in conjunction with Figure of description, the present invention is further elaborated.
As shown in Figure 3, a kind of aeroengine thrust transition of the present invention automatic judging method comprises the following steps:
The parameter oscillography function of application test bay data acquisition system (DAS), checks and accepts figure as typical curve input computer using the normal rated thrust transient response of aeromotor;
Thrust transient test is carried out to aeromotor, mobile throttle lever;
When throttle lever traveling time conforms with the regulations, the actual thrust transient response curve (as shown in Figure 4) of aeromotor is plotted in the normal rated thrust transient response examination figure of aeromotor, obtains the automatic interpretation curve map (as shown in Figure 5) of aeromotor actual thrust response transition curve and typical curve;
Each phase actual thrust in the same time and the size of normal rated thrust is contrasted in above-mentioned relation figure;
When actual thrust is all more than or equal to normal rated thrust to each phase in the same time, in automatic interpretation curve map, provide the conclusion that thrust is qualified;
Otherwise, when actual thrust is less than normal rated thrust to a certain phase in the same time, in automatic interpretation curve map, provide the underproof conclusion of thrust.
If throttle lever traveling time is against regulation, then do not draw actual thrust transient response curve.
The present invention utilizes test bay data acquisition system (DAS) to carry out secondary development, establishment thrust transient response characteristic oscillography curve, and normal rated thrust is responded examination figure and be plotted in oscillography curve, as criterion.Whether start to draw by the rate of change automatic identification oscillography curve of engine power control arm, meet the requirements, start to draw the actual dynamic response characteristic curve of engine, then whether qualified by checking and accepting curve evaluation family curve, and provide conclusion; Undesirable then not curve plotting else if, shows to promote throttle lever speed slow, need re-start thrust transient test.
The present invention is in practical operation, and first, the parameter oscillography function of application test bay data acquisition system (DAS), checks and accepts curve using the thrust shown in Fig. 1 and normal rated thrust response checks and accepts figure input computer as basis of reference.
Then, drawn in FIG by actual for engine test run thrust data, the engine actual thrust obtained as shown in Figure 5 responds the automatic interpretation curve map of transition curve and typical curve.
The evaluation of thrust transition comprises time parameter and thrust parameter, and namely whether throttle lever traveling time meets the requirements, and two is whether each point thrust is greater than typical curve.Throttle lever traveling time judges when drawing actual thrust response transition curve, and after only having throttle lever traveling time to conform with the regulations, just start to draw actual thrust response transition curve, no person does not draw this curve.Thrust standard is judged by the difference comparing actual thrust and normal rated thrust on random time point, and the difference of random time point should be greater than zero.
Application the inventive method can realize the thrust dynamic response characteristic of real-time automatic evaluation engine, saves manpower and time, and reduces test run number of times and the duration of runs in engine works, reduces engine production repair cost.
Claims (3)
1. an aeroengine thrust transition automatic judging method, is characterized in that comprising the following steps:
The parameter oscillography function of application test bay data acquisition system (DAS), checks and accepts figure as typical curve input computer using the normal rated thrust transient response of aeromotor;
Thrust transient test is carried out to aeromotor, mobile throttle lever;
When throttle lever traveling time conforms with the regulations, the actual thrust transient response curve of aeromotor is plotted in the normal rated thrust transient response examination figure of aeromotor, obtains the automatic interpretation curve map of aeromotor actual thrust response transition curve and typical curve;
The size of synchronization actual thrust and normal rated thrust is contrasted in above-mentioned relation figure;
When actual thrust is more than or equal to normal rated thrust, in automatic interpretation curve map, provide the conclusion that thrust is qualified.
2., by aeroengine thrust transition automatic judging method according to claim 1, it is characterized in that:
When actual thrust is less than normal rated thrust, in automatic interpretation curve map, provide the underproof conclusion of thrust.
3., by aeroengine thrust transition automatic judging method according to claim 1, it is characterized in that: if throttle lever traveling time is against regulation, then do not draw actual thrust transient response curve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410628140.3A CN104359678A (en) | 2014-11-10 | 2014-11-10 | Method for automatically judging thrust transient of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410628140.3A CN104359678A (en) | 2014-11-10 | 2014-11-10 | Method for automatically judging thrust transient of aeroengine |
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| Publication Number | Publication Date |
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| CN104359678A true CN104359678A (en) | 2015-02-18 |
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| CN201410628140.3A Pending CN104359678A (en) | 2014-11-10 | 2014-11-10 | Method for automatically judging thrust transient of aeroengine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300699A (en) * | 2015-11-20 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for evaluating engine thrust transient performance |
| CN112431676A (en) * | 2020-11-19 | 2021-03-02 | 中国航发沈阳发动机研究所 | Self-protection control method for aircraft engine in non-warmed state |
| CN114544180A (en) * | 2021-12-29 | 2022-05-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Engine large throttle evaluation method and device |
-
2014
- 2014-11-10 CN CN201410628140.3A patent/CN104359678A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300699A (en) * | 2015-11-20 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for evaluating engine thrust transient performance |
| CN105300699B (en) * | 2015-11-20 | 2017-08-25 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of assessment method of motor power transient performance |
| CN112431676A (en) * | 2020-11-19 | 2021-03-02 | 中国航发沈阳发动机研究所 | Self-protection control method for aircraft engine in non-warmed state |
| CN112431676B (en) * | 2020-11-19 | 2022-03-04 | 中国航发沈阳发动机研究所 | Self-protection control method for aircraft engine in non-warmed state |
| CN114544180A (en) * | 2021-12-29 | 2022-05-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Engine large throttle evaluation method and device |
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Application publication date: 20150218 |
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| RJ01 | Rejection of invention patent application after publication |