CN105651520A - Positioning method for vibration fault of external accessory of aircraft engine - Google Patents
Positioning method for vibration fault of external accessory of aircraft engine Download PDFInfo
- Publication number
- CN105651520A CN105651520A CN201610114871.5A CN201610114871A CN105651520A CN 105651520 A CN105651520 A CN 105651520A CN 201610114871 A CN201610114871 A CN 201610114871A CN 105651520 A CN105651520 A CN 105651520A
- Authority
- CN
- China
- Prior art keywords
- aero
- engine
- external accessory
- under
- normal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
Abstract
The invention discloses a positioning method for the vibration fault of an external accessory of an aircraft engine. The method includes the following steps that a data acquisition instrument obtains the difference value between vibration information of a normal external accessory of the aircraft engine and vibration information of a to-be-positioned external accessory of the aircraft engine in the same state, and then whether the vibration fault happens to the to-be-positioned external accessory of the aircraft engine or not is judged according to the difference value between vibration information of the normal external accessory of the aircraft engine and vibration information of the to-be-positioned external accessory of the aircraft engine in the same state. Positioning of the vibration fault of the external accessory of the aircraft engine can be rapidly completed.
Description
Technical field
The invention belongs to aero-engine field, relate to the localization method of a kind of aero-engine external accessory vibration fault.
Background technology
The troubleshooting method that aero-engine external accessory vibration fault is conventional is to fix a breakdown by changing related accessories, but for the clear and definite location of failure cause neither one, does not namely find vibration source. For some simple vibration faults, it is possible to just can be got rid of by renewal part, but for some complex vibration faults, just cannot well be completed failture evacuation by the method, owing to failure cause cannot be positioned, cause that vibration fault frequently occurs.
Summary of the invention
It is an object of the invention to the shortcoming overcoming above-mentioned prior art, it is provided that the localization method of a kind of aero-engine external accessory vibration fault, the method can quickly finish the location of aero-engine external accessory vibration fault.
For reaching above-mentioned purpose, the localization method of aero-engine external accessory vibration fault of the present invention comprises the following steps:
1) normal aero-engine is chosen, vibrating sensor is fixed on the external accessory of normal aero-engine, under different conditions, normal aero-engine is carried out test run respectively, in commissioning process, when after normal aero-engine stable operation, detect the vibration information on normal aero-engine external accessory by vibrating sensor, and the vibration information on normal aero-engine external accessory is forwarded on data collecting instrument;
2) vibrating sensor is fixed on the external accessory of aero-engine to be positioned, under different conditions, aero-engine to be positioned is carried out test run respectively, in commissioning process, when after aero-engine stable operation to be positioned, detect the vibration information on aero-engine external accessory to be positioned by vibrating sensor, and the vibration information on aero-engine external accessory to be positioned is forwarded on data collecting instrument;
3) data collecting instrument obtains the difference under same state between vibration information and the vibration information of aero-engine external accessory to be positioned of normal aero-engine external accessory, then judges whether aero-engine external accessory to be positioned vibration fault occurs according to the difference between vibration information and the vibration information of aero-engine external accessory to be positioned of aero-engine external accessory normal under equal state.
Step 1) in vibrating sensor is bonded on normal aero-engine external accessory;
Step 2) in vibrating sensor bond on aero-engine external accessory to be positioned.
Step 1) in respectively under 60% high pressure rotating speed, normal aero-engine is carried out test run under 65% high pressure rotating speed, under 75% high pressure rotating speed, under 85% high pressure rotating speed, under 90% high pressure rotating speed and under 95% high pressure rotating speed;
Step 2) in respectively under 60% high pressure rotating speed, aero-engine to be positioned is carried out test run under 65% high pressure rotating speed, under 75% high pressure rotating speed, under 85% high pressure rotating speed, under 90% high pressure rotating speed and under 95% high pressure rotating speed.
Step 1) in when after normal aero-engine stable operation 1min, detect the vibration information on normal aero-engine external accessory by vibrating sensor;
Step 2) in when after aero-engine stable operation 1min to be positioned, detect the vibration information on aero-engine external accessory to be positioned by vibrating sensor.
The method have the advantages that
The localization method of aero-engine external accessory vibration fault of the present invention is when concrete operations, by gather under different conditions normal aero-engine external accessory vibration information in commissioning process as check sample, gather the aero-engine external accessory to be positioned vibration information in commissioning process under different conditions again, then judge whether aero-engine to be positioned vibration fault occurs according to the difference between vibration information and the vibration information of aero-engine external accessory to be positioned of aero-engine external accessory normal under equal state, simple to operate, fast, and aircraft engine parts need not be decomposed and can reach quickly to position the purpose of fault, have simple to operate, location low cost and other advantages.
Accompanying drawing explanation
Fig. 1 is the flow chart of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail:
With reference to Fig. 1, the localization method of aero-engine external accessory vibration fault of the present invention comprises the following steps:
1) normal aero-engine is chosen, vibrating sensor is fixed on the external accessory of normal aero-engine, under different conditions, normal aero-engine is carried out test run respectively, in commissioning process, when after normal aero-engine stable operation, detect the vibration information on normal aero-engine external accessory by vibrating sensor, and the vibration information on normal aero-engine external accessory is forwarded on data collecting instrument;
2) vibrating sensor is fixed on the external accessory of aero-engine to be positioned, under different conditions, aero-engine to be positioned is carried out test run respectively, in commissioning process, when after aero-engine stable operation to be positioned, detect the vibration information on aero-engine external accessory to be positioned by vibrating sensor, and the vibration information on aero-engine external accessory to be positioned is forwarded on data collecting instrument;
3) data collecting instrument obtains the difference under same state between vibration information and the vibration information of aero-engine external accessory to be positioned of normal aero-engine external accessory, then judges whether aero-engine external accessory to be positioned vibration fault occurs according to the difference between vibration information and the vibration information of aero-engine external accessory to be positioned of aero-engine external accessory normal under equal state. Concrete, when described difference is more than preset range, then illustrate that vibration fault occurs in this aero-engine external accessory to be positioned, when the difference obtained under any one state is more than preset range, then illustrate that vibration fault occurs in this aero-engine external accessory to be positioned.
Step 1) in vibrating sensor is bonded on normal aero-engine external accessory;
Step 2) in vibrating sensor bond on aero-engine external accessory to be positioned.
Step 1) in respectively under 60% high pressure rotating speed, normal aero-engine is carried out test run under 65% high pressure rotating speed, under 75% high pressure rotating speed, under 85% high pressure rotating speed, under 90% high pressure rotating speed and under 95% high pressure rotating speed;
Step 2) in respectively under 60% high pressure rotating speed, aero-engine to be positioned is carried out test run under 65% high pressure rotating speed, under 75% high pressure rotating speed, under 85% high pressure rotating speed, under 90% high pressure rotating speed and under 95% high pressure rotating speed.
Step 1) in when after normal aero-engine stable operation 1min, detect the vibration information on normal aero-engine external accessory by vibrating sensor;
Step 2) in when after aero-engine stable operation 1min to be positioned, detect the vibration information on aero-engine external accessory to be positioned by vibrating sensor.
Embodiment one
For engine fuel pressure difference signal device position abnormal vibration fault, this electromotor is in the use procedure of outfield, continuously because vibration cause causes that signal indicator is damaged in 7 months, cause the fuel oil bright fault of pressure reduction stand by lamp, still, the use of electromotor has been had a strong impact on by fault after changing multiple fuel oil pressure difference signal device. In order to find out failure cause, carry out fault location according to the present invention, wherein choose normal two electromotor intermediate fuel oil pressure difference signal devices and carry out vibration-testing, shown in Results of Vibration such as table 1 and table 2:
Table 1
Table 2
Can be seen that from table 1 and table 2, the vibration total amount of normal engine is less with trial condition difference amplitude of variation, maximum is reached when adding gentle maximum military state, it is about about 5g, and each frequency component that vibration total amount comprises under each trial condition is distributed discrete, and each frequency component values is suitable, there is no prominent characteristic frequency components.
The fuel oil pressure difference signal device employing of sick engine is reassembled carry out vibration measurement under latter two state in previous status and decomposition cam box, shown in concrete measurement data such as table 3 and table 4:
Table 3
Table 4
By contrasting vibration measurement it can be seen that under this electromotor previous status the vibration compared with normal electromotor at fuel oil pressure difference signal device position abnormal, total amount is big and characteristic frequency highlights in vibration; And after being reassembled by decomposition cam box, under each steady statue of engine test, fuel oil pressure difference signal device vibration total amount is less with trial condition difference amplitude of variation, vibration total amount reduction and each frequency component distribution comprised are discrete, test run vibration regularity is basically identical with the vibration regularity of normal engine, it is possible to determine that the fuel oil pressure difference signal device abnormal vibration fault of sick engine causes owing to the assembling of engine cam case is improper.
Claims (4)
1. the localization method of an aero-engine external accessory vibration fault, it is characterised in that comprise the following steps:
1) normal aero-engine is chosen, vibrating sensor is fixed on the external accessory of normal aero-engine, under different conditions, normal aero-engine is carried out test run respectively, in commissioning process, when after normal aero-engine stable operation, detect the vibration information on normal aero-engine external accessory by vibrating sensor, and the vibration information on normal aero-engine external accessory is forwarded on data collecting instrument;
2) vibrating sensor is fixed on the external accessory of aero-engine to be positioned, under different conditions, aero-engine to be positioned is carried out test run respectively, in commissioning process, when after aero-engine stable operation to be positioned, detect the vibration information on aero-engine external accessory to be positioned by vibrating sensor, and the vibration information on aero-engine external accessory to be positioned is forwarded on data collecting instrument;
3) data collecting instrument obtains the difference under same state between vibration information and the vibration information of aero-engine external accessory to be positioned of normal aero-engine external accessory, then judges whether aero-engine external accessory to be positioned vibration fault occurs according to the difference between vibration information and the vibration information of aero-engine external accessory to be positioned of aero-engine external accessory normal under equal state.
2. the localization method of aero-engine external accessory vibration fault according to claim 1, it is characterised in that
Step 1) in vibrating sensor is bonded on normal aero-engine external accessory;
Step 2) in vibrating sensor bond on aero-engine external accessory to be positioned.
3. the localization method of aero-engine external accessory vibration fault according to claim 1, it is characterised in that
Step 1) in respectively under 60% high pressure rotating speed, normal aero-engine is carried out test run under 65% high pressure rotating speed, under 75% high pressure rotating speed, under 85% high pressure rotating speed, under 90% high pressure rotating speed and under 95% high pressure rotating speed;
Step 2) in respectively under 60% high pressure rotating speed, aero-engine to be positioned is carried out test run under 65% high pressure rotating speed, under 75% high pressure rotating speed, under 85% high pressure rotating speed, under 90% high pressure rotating speed and under 95% high pressure rotating speed.
4. the localization method of aero-engine external accessory vibration fault according to claim 1, it is characterised in that
Step 1) in when after normal aero-engine stable operation 1min, detect the vibration information on normal aero-engine external accessory by vibrating sensor;
Step 2) in when after aero-engine stable operation 1min to be positioned, detect the vibration information on aero-engine external accessory to be positioned by vibrating sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610114871.5A CN105651520A (en) | 2016-03-01 | 2016-03-01 | Positioning method for vibration fault of external accessory of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610114871.5A CN105651520A (en) | 2016-03-01 | 2016-03-01 | Positioning method for vibration fault of external accessory of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105651520A true CN105651520A (en) | 2016-06-08 |
Family
ID=56492911
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610114871.5A Pending CN105651520A (en) | 2016-03-01 | 2016-03-01 | Positioning method for vibration fault of external accessory of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105651520A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106482828A (en) * | 2016-11-25 | 2017-03-08 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of checkout and diagnosis device and method of Fault Diagnosis of Aeroengines |
| CN111795824A (en) * | 2019-04-09 | 2020-10-20 | 中国航发商用航空发动机有限责任公司 | Fault diagnosis method and system for mechanical power system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008128742A (en) * | 2006-11-17 | 2008-06-05 | Toyota Central R&D Labs Inc | Apparatus and method for analyzing vibration in rotating structure |
| CN101936812A (en) * | 2010-08-25 | 2011-01-05 | 重庆大学 | Method for detecting working state of engine of armored vehicle |
| CN102270271A (en) * | 2011-05-03 | 2011-12-07 | 北京中瑞泰科技有限公司 | Equipment failure early warning and optimizing method and system based on similarity curve |
| CN103218464A (en) * | 2013-03-23 | 2013-07-24 | 中国水利电力物资有限公司 | Wind turbine generator state-based wind turbine generator data storage method and system |
| CN103226651A (en) * | 2013-03-23 | 2013-07-31 | 中国水利电力物资有限公司 | Wind turbine state evaluation and early-warning method and system based on similarity statistics |
| CN103940611A (en) * | 2014-04-09 | 2014-07-23 | 中国水利水电科学研究院 | Self-adaptive anomaly detection method for rolling bearing of wind generator set under variable working conditions |
| CN104458252A (en) * | 2014-08-30 | 2015-03-25 | 吉林大学 | Method for monitoring running state of high-speed train gear box |
-
2016
- 2016-03-01 CN CN201610114871.5A patent/CN105651520A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008128742A (en) * | 2006-11-17 | 2008-06-05 | Toyota Central R&D Labs Inc | Apparatus and method for analyzing vibration in rotating structure |
| CN101936812A (en) * | 2010-08-25 | 2011-01-05 | 重庆大学 | Method for detecting working state of engine of armored vehicle |
| CN102270271A (en) * | 2011-05-03 | 2011-12-07 | 北京中瑞泰科技有限公司 | Equipment failure early warning and optimizing method and system based on similarity curve |
| CN103218464A (en) * | 2013-03-23 | 2013-07-24 | 中国水利电力物资有限公司 | Wind turbine generator state-based wind turbine generator data storage method and system |
| CN103226651A (en) * | 2013-03-23 | 2013-07-31 | 中国水利电力物资有限公司 | Wind turbine state evaluation and early-warning method and system based on similarity statistics |
| CN103940611A (en) * | 2014-04-09 | 2014-07-23 | 中国水利水电科学研究院 | Self-adaptive anomaly detection method for rolling bearing of wind generator set under variable working conditions |
| CN104458252A (en) * | 2014-08-30 | 2015-03-25 | 吉林大学 | Method for monitoring running state of high-speed train gear box |
Non-Patent Citations (1)
| Title |
|---|
| 邓明 等: "《航空发动机故障诊断》", 30 June 2012, 北京航空航天大学出版社 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106482828A (en) * | 2016-11-25 | 2017-03-08 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of checkout and diagnosis device and method of Fault Diagnosis of Aeroengines |
| CN111795824A (en) * | 2019-04-09 | 2020-10-20 | 中国航发商用航空发动机有限责任公司 | Fault diagnosis method and system for mechanical power system |
| CN111795824B (en) * | 2019-04-09 | 2022-03-04 | 中国航发商用航空发动机有限责任公司 | Fault diagnosis method and system for mechanical power system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Leclère et al. | A multi-order probabilistic approach for Instantaneous Angular Speed tracking debriefing of the CMMNO׳ 14 diagnosis contest | |
| DE112012003854T5 (en) | Systems and methods for diagnosing a motor | |
| US10871409B2 (en) | SMD-coil-based torque-sensor for tangential field measurement | |
| CA2398248A1 (en) | Diagnostic method and system for turbine engines | |
| CN102967793A (en) | Open-circuit short-circuit detection circuit of car-mounted terminal antenna | |
| CN105651520A (en) | Positioning method for vibration fault of external accessory of aircraft engine | |
| EP2905452A3 (en) | Asil B-compliant implementation of automotive safety-related functions by means of a high diagnosability, quality managed-compliant integrated circuit | |
| US9188633B2 (en) | Power supply apparatus for test apparatus | |
| CN103344398A (en) | Method for testing damping property of on-line monitoring device of power transformation equipment | |
| US20200191856A1 (en) | High frequency arc fault detection | |
| CN108021122B (en) | Vibration test fault diagnosis method for aircraft engine | |
| CN105675304A (en) | Automobile engine on-line monitoring system | |
| CN114544188A (en) | Vibration fluctuation fault identification and elimination method caused by multi-source beat vibration of aircraft engine | |
| CN106525223A (en) | Offline detection method for abnormal noise of gear assembly | |
| Butov et al. | Comparison of end of line tests for serial production of electric motors in hybrid truck applications | |
| CN107918080B (en) | Sensor connection state detection method and device and sensor | |
| CN104358823B (en) | A kind of method of checking engine vibration-damping crank pulley natural frequency detection facility accuracy | |
| CN104849070B (en) | A kind of smoking car fault test set and detection method | |
| KR101713701B1 (en) | Apparatus for adjustment motor position signal of green car and method thereof | |
| CN202066692U (en) | Novel test beam apparatus suitable for test of engine pedestal | |
| US9671454B2 (en) | Method for detecting a device that generates spurious signals in an electrical network, an electrical system and an aircraft | |
| CN103954451B (en) | The troubleshooting method of a kind of engine cross matching in place | |
| CN204129183U (en) | A kind of air pressure switch debugging apparatus | |
| US11054340B2 (en) | Parametric trending architecture concept and design | |
| CN103576732B (en) | Throw load voltage wave suppression device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160608 |