CN109655274A - A kind of environmental tester having failure of pump diagnostic function - Google Patents
A kind of environmental tester having failure of pump diagnostic function Download PDFInfo
- Publication number
- CN109655274A CN109655274A CN201710941812.XA CN201710941812A CN109655274A CN 109655274 A CN109655274 A CN 109655274A CN 201710941812 A CN201710941812 A CN 201710941812A CN 109655274 A CN109655274 A CN 109655274A
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- China
- Prior art keywords
- failure
- fuel pump
- pump
- pressure
- main fuel
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Classifications
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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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B51/00—Testing machines, pumps, or pumping installations
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The present invention relates to a kind of environmental testers for having failure of pump diagnostic function, more particularly to have the aero-engine fuel control system high and low temperature exerciser of online fault detection demand.The environmental tester is refered in particular to for aero-engine fuel control system high temperature, low temperature and vibration test, subjects are aero-engine main fuel pump, it is characterized in that: it is provided with pressure sensor at away from main fuel pump outlet 10-15cm, processor judges the failure of main fuel pump by the signal that pressure sensor acquires；More than two pressure sensors are evenly equipped on main fuel pump outlet fuel line cross section.By to fuel pump outlet pressure signal Pulsation analysis during test, fault diagnosis can be carried out to the fuel pump for carrying out environmental test, confirm time of failure, avoid failure after there is still a need for after completing environmental test, overhaul could be carried out to main fuel pump, the problem of being confirmed whether to break down, and can not judging time of failure after confirmation failure.
Description
Technical field
The present invention relates to a kind of environmental testers for having failure of pump diagnostic function, more particularly to have online fault detection to need
The aero-engine fuel control system high and low temperature exerciser asked.
Background technique
The aero-engine course of work is extremely complex, and fuel control system is a key for determining aero-engine performance
System, fuel control system are made of fuel pump and several adjusters.Aero-engine fuel pump working environment is harsh, performance is wanted
Ask high, it is therefore desirable to carry out a large amount of indispensable but require stringent environmental test.
But since aero-engine vehicle fuel pump structure form is complicated, assembly technology is stringent, except environmental test completion is laggard
Outside row overhaul, without preferable method for diagnosing faults.And overhaul takes time and effort, and can not accomplish to during test
Pump abrasion condition is analyzed.It is therefore desirable to have more rationally effective diagnostic mode carries out failure of pump diagnosis.
Summary of the invention
The purpose of the present invention: provide it is a kind of have environmental test is carried out to aero-engine fuel control system each attachment
Function is provided simultaneously with the environmental tester for carrying out on-line fault diagnosis function to the fuel pump in environmental test, solves existing skill
The technical problem that the main fuel pump malfunction elimination period is long in art, difficulty is big.
Technical solution of the present invention: a kind of environmental tester having failure of pump diagnostic function, the environmental tester
It refers in particular to for aero-engine fuel control system high temperature, low temperature and vibration test, subjects are aero-engine main fuel
Pump, it is characterized in that: it is provided with pressure sensor at away from main fuel pump outlet 10-15cm, processor is adopted by pressure sensor
The signal of collection judges the failure of main fuel pump；
More than two pressure sensors are evenly equipped on main fuel pump outlet fuel line cross section.
It is preferably, uniformly distributed on main fuel pump outlet fuel line cross section that there are four pressure sensors.
Preferably, the regular shape container of both ends connection oil circuit is provided on the main fuel pump outlet fuel pipeline,
Pressure sensor is fixed on the container by flanged joint；
The slot of accommodating pressure sensor connector is provided on the container, the bottom of slot is connect with side wall by arc transition,
The radius R of the circular arc is greater than 1mm.
Preferably, the sample frequency of the pressure sensor is 1~5KHz, range 0-25MPa.
Preferably, Fast Fourier Transform (FFT) is carried out to the Pressure Fluctuation Signal of pressure sensor acquisition, obtains main fuel pump
Outlet pressure frequency domain character judges main fuel pump failure according to the frequency domain character.
Preferably, the electric signal output area of pressure sensor is 0-100mv.
Beneficial effects of the present invention: the present invention, can by fuel pump outlet pressure signal Pulsation analysis during test
To carry out fault diagnosis to the fuel pump for carrying out environmental test, confirms time of failure, avoid after breaking down still
It needs after completing environmental test, overhaul could be carried out to main fuel pump, be confirmed whether to break down, and after confirmation failure
The problem of can not judging time of failure.
Detailed description of the invention
Fig. 1 is the principle of the present invention schematic diagram；
Fig. 2 is that the both ends being arranged on main fuel pump outlet fuel pipe connect the regular shape container schematic diagram of oil circuit
Fig. 3 is pressure sensor mounting structure schematic diagram；
Fig. 4 is pressure fluctuation frequency domain character schematic diagram when certain type fuel pump works normally；
Pressure fluctuation frequency domain character schematic diagram when Fig. 5 is certain type fuel pump partial friction.
In figure: 1- gearbox；2- mandrel connector；3- motor；4- speed probe；5- environmental cabinet；6- fuel pump；7- combustion
Oil pump inlet pressure sensor；8- fuel pump import oily filter；9- fuel pump inlet temperature sensor；10- fuel pump outlet oily filter；
11- primary booster pump；12- fuel tank；13- fuel pump outlet pressure sensor；14- processing module；15- container.
Specific embodiment
The principle of the present invention, structure and specific implementation measure are described further in conjunction with attached drawing.
Fig. 1 is the principle of the present invention schematic diagram.
Environmental cabinet 5, which has, provides the functions such as heating, cooling, vibration to box house environment and fuel medium.
Fuel pump 6 by screw, quick-release ring or other be fixedly mounted in environmental cabinet 5, motor 3 passes through axis connection
Device 2 and gearbox 1 drive fuel pump to be operated, at this time primary booster pump 11 extracted from fuel tank 12 No. 3 jet fuels or its
His type fuel oil, fuel oil lead to fuel pump 6 after being filtered by fuel pump import oily filter 8, and fuel pump import oily filter 8 is avoided that
Alien material enters fuel pump 6.
The import of fuel pump 6 is passed equipped with speed probe 4, fuel pump inlet pressure sensor 7 and fuel pump inlet temperature
Sensor 9.Fuel pump inlet pressure sensor 7 detects the pressure of fuel oil pump inlet medium, if being unsatisfactory for the operating condition of pump, leads to
Cross the pressure for adjusting primary 11 revolving speed of booster pump and then adjusting fuel oil pump inlet medium.Fuel pump inlet temperature sensor 9 detects
The temperature of fuel oil pump inlet medium adjusts the temperature of fuel oil pump inlet medium by environmental cabinet 5 if being unsatisfactory for the operating condition of pump
Degree, speed probe 4 acquire fuel oil revolution speed.
No. 3 jet fuels return to fuel tank 12 by fuel pump outlet oily filter 10, complete fuel pump working cycles, and fuel oil pumps out
Mouth oily filter 10 avoids the foreign matter generated in test from entering fuel tank 12.
In the above-mentioned course of work, increase fuel pump outlet pressure sensor 13, fuel pump outlet in the outlet of fuel pump 6
Pressure sensor 13 has the function of collecting fuel pump outlet pressure fluctuation signal.
Fuel pump outlet pressure sensor 13 on pump discharge pipe road should be greater than two, and is evenly arranged on main fuel and pumps out
On mouth fuel pipe cross section, except the event of equipment report can be caused to avoid 13 failure of fuel pump outlet pressure sensor, equipment is improved
Reliability outside, moreover it is possible to according to the uniformly distributed collected pressure fluctuation signal difference of multiple fuel pump outlet pressure sensors 13,
Cross interference caused by filtering out the outer other signals of fuel oil fluctuating signal.
Uniformly distributed four pressure sensors, can be effectively reduced exclusion fuel pipe on main fuel pump outlet fuel line cross section
The difficulty of the circumferential other signal interferences in road, has preferable cost performance.
The regular shape container 15 of both ends connection oil circuit, regular shape are provided on the main fuel pump outlet fuel pipeline
Shape container can be the shapes such as square, cuboid, cylindrical body, and wherein the processing is simple for square, and cylinder volume is smaller, weight
It is relatively light.For purposes of illustration only, the present invention is by taking square as an example；Pressure sensor is fixed on the container, and fixed form includes spiral shell
The modes such as line connection, flanged joint, crimping, flanged joint dismounting is simple, pressure resistance is higher, therefore preferably flanged joint, such as Fig. 2
It is shown,；
As shown in figure 3, the vessel surface is provided with the slot of accommodating pressure sensor pressure-sensitive part, have inside the container
Arbitrary section product not less than the cavity of main fuel pump outlet fuel pipe section product, accommodates the slot of pressure sensor pressure-sensitive part
It is connected with the cavity inside container, which can pass through the chamber inside the slot and container of accommodating pressure sensor pressure-sensitive part
Connected access pressure signal caused by the pipeline interference of body is filtered.
The trench bottom of accommodating pressure sensor pressure-sensitive part is connect with side wall by arc transition, the radius R of the circular arc
Greater than 1mm, the radius R of circular arc, which is greater than 1mm, can guarantee the container normal work under the conditions of hot environment and fuel pressure fluctuate
Make.
According to for statistical analysis and to the following fuel pump development prediction to existing fuel pump, the pressure sensor is adopted
Sample frequency is 1~5KHz, and range is that 0-25MPa can preferably meet existing and future usage demand.
The electric signal output area of pressure sensor is usually 0-4mv or 0-5V, considers pressure sensor explosion-proof demand
And resolution requirements, the preferred output area of electric signal output area of pressure sensor are 0-100mv.
The collected fuel pump outlet pressure fluctuation signal of fuel pump outlet pressure sensor 13 of pump discharge pipe road passes through
14 Fast Fourier Transform (FFT) of processing module, window Fourier transform, wavelet transformation etc. have the processing method of frequency-domain analysis function
Afterwards, achievable fuel pump on-line fault diagnosis.
According to equipment working principle, it is preferable to use Fast Fourier Transform (FFT), can generate going out for the fuel pump 6 on frequency domain in real time
Mouth pressure fluctuation signal.According to the working principle of fuel pump 6, when different faults occurs in fuel pump 6, the outlet pressure of fuel pump 6
Different variations can occur for power ripple frequency, and this variation is more obvious on frequency domain, such as when eccentric wear occurs for gear of fuel pump
When, fuel pressure ripple frequency can decline (see Fig. 4, Fig. 5), so as to the foundation as fuel pump on-line fault diagnosis.
Claims (6)
1. a kind of environmental tester for having failure of pump diagnostic function, the environmental tester refers in particular to fire for aero-engine
The online high temperature of EFM Electronic Fuel Management, low temperature and vibration test, subjects be aero-engine main fuel pump, it is characterized in that: away from
It is provided with pressure sensor at main fuel pump outlet 10-15cm, processor judges main combustion by the signal that pressure sensor acquires
The failure of oil pump；
More than two pressure sensors are evenly equipped on main fuel pump outlet fuel line cross section.
2. a kind of environmental tester for having failure of pump diagnostic function according to claim 1, it is characterized in that: in main fuel
It is uniformly distributed on pump discharge fuel pipe cross section that there are four pressure sensors.
3. a kind of environmental tester for having failure of pump diagnostic function according to claim 1, it is characterized in that: the master
The regular shape container of both ends connection oil circuit is provided on fuel pump outlet fuel pipe, pressure sensor is solid by flanged joint
Determine on the container；
The slot of accommodating pressure sensor connector is provided on the container, the bottom of slot is connect with side wall by arc transition, described
The radius R of circular arc is greater than 1mm.
4. a kind of environmental tester for having failure of pump diagnostic function according to claim 1, it is characterized in that: the pressure
The sample frequency of sensor is 1~5KHz, range 0-25MPa.
5. a kind of environmental tester for having failure of pump diagnostic function according to claim 1, it is characterized in that: pressure is passed
The Pressure Fluctuation Signal of sensor acquisition carries out Fast Fourier Transform (FFT), main fuel pump outlet pressure frequency domain character is obtained, according to this
Frequency domain character judges main fuel pump failure.
6. a kind of environmental tester for having failure of pump diagnostic function according to claim 1, it is characterized in that: pressure sensing
The electric signal output area of device is 0-100mv.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710941812.XA CN109655274A (en) | 2017-10-11 | 2017-10-11 | A kind of environmental tester having failure of pump diagnostic function |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710941812.XA CN109655274A (en) | 2017-10-11 | 2017-10-11 | A kind of environmental tester having failure of pump diagnostic function |
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| Publication Number | Publication Date |
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| CN109655274A true CN109655274A (en) | 2019-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710941812.XA Pending CN109655274A (en) | 2017-10-11 | 2017-10-11 | A kind of environmental tester having failure of pump diagnostic function |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112696301A (en) * | 2020-12-15 | 2021-04-23 | 安徽宝隽机车部件有限公司 | Intermittent soft fault detection system of electronic injection fuel pump |
| CN115585066A (en) * | 2022-11-01 | 2023-01-10 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Integrated intelligent fuel pump and control method thereof |
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| CN201568280U (en) * | 2009-11-10 | 2010-09-01 | 江西洪都航空工业集团有限责任公司 | Miniaturized testing device for oil fuel booster pump of aircraft |
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| CN106801670A (en) * | 2015-11-26 | 2017-06-06 | 中国人民解放军军械工程学院 | Life for Hydraulic Pump testing stand |
| CN107036816A (en) * | 2016-11-17 | 2017-08-11 | 重庆工商大学 | A kind of Aero-engine Bearing method for diagnosing faults |
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- 2017-10-11 CN CN201710941812.XA patent/CN109655274A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201130424Y (en) * | 2007-12-15 | 2008-10-08 | 银川高新区慧泽园科技有限公司 | System for monitoring dynamic quality of diesel locomotive |
| CN101571120A (en) * | 2009-05-31 | 2009-11-04 | 北京航空航天大学 | Hierarchical cluster aviation pump multiple fault diagnostic method based on frequency multiplication relative energy sum |
| CN201568280U (en) * | 2009-11-10 | 2010-09-01 | 江西洪都航空工业集团有限责任公司 | Miniaturized testing device for oil fuel booster pump of aircraft |
| CN202420800U (en) * | 2011-12-12 | 2012-09-05 | 济南吉利汽车有限公司 | Air tightness detection device for fuel tank |
| CN204731026U (en) * | 2015-06-02 | 2015-10-28 | 中航飞机股份有限公司西安飞机分公司 | A kind of airplane engine fuel oil analog control system |
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| CN206221115U (en) * | 2016-09-30 | 2017-06-06 | 中航商用航空发动机有限责任公司 | The feeding pressure stabilizing device of aircraft engine test stand fuel service system |
| CN107036816A (en) * | 2016-11-17 | 2017-08-11 | 重庆工商大学 | A kind of Aero-engine Bearing method for diagnosing faults |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112696301A (en) * | 2020-12-15 | 2021-04-23 | 安徽宝隽机车部件有限公司 | Intermittent soft fault detection system of electronic injection fuel pump |
| CN115585066A (en) * | 2022-11-01 | 2023-01-10 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Integrated intelligent fuel pump and control method thereof |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190419 |
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| RJ01 | Rejection of invention patent application after publication |