CN104330262B - Aero-engine combustion oil system assay device - Google Patents
Aero-engine combustion oil system assay device Download PDFInfo
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- CN104330262B CN104330262B CN201410568092.3A CN201410568092A CN104330262B CN 104330262 B CN104330262 B CN 104330262B CN 201410568092 A CN201410568092 A CN 201410568092A CN 104330262 B CN104330262 B CN 104330262B
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Abstract
The present invention relates to a kind of aero-engine combustion oil system assay device, including connecting interface and control system, it is provided with pressure and temp composite module arranged in pairs on described connection interface, is connected stand with aero-engine combustion oil system and test-bed respectively and connects；Control system includes that the power supply interface of master control circuit board is connected with electric power system, signal input output interface connects with the network interface being connected on interface, every pair of pressure and temp composite module is connected with conditioning module, and power supply interface, conditioning module, modulate circuit are connected with master control circuit board respectively.The present invention guarantee test equipment connect soon safe and reliable, convenient connect soon while, can directly monitor the combustion temperature of oil system, pressure and other parameters, and at the aspect such as safety, sealing, there is good performance, preferably achieve the intellectuality of quick access device, complete to meet the requirement that Aero Engine Testing quickly connects.
Description
Technical field
The present invention relates to a kind of aero-engine combustion oil system assay device, for aero-engine combustion oil system and examination
Test the parameter measurement quickly connecting and realize firing oil system of stand.
Background technology
Aero-engine combustion oil system in process of scientific research or after a repair, needs the test before installing, with inspection
Whether the parameters of system meets the requirements.Test is typically carried out on Special test platform, and described testing stand is provided with hydraulic pressure
System, provides combustion lubricating oil for testpieces.In process of the test, need to measure the temperature of hydraulic system, pressure and other parameters, in order to
Detection controls electromotor and the various duties of test bay hydraulic system.The attachment means of aero-engine combustion oil system,
On the premise of guaranteeing not change electromotor combustion oil system performance, the fast of completion system connects in succession, fast with guarantee test equipment
Speed, stable, reliable requirement.Current aero-engine combustion oil system and the attachment means of testing stand, simply will fire lubricating oil
System is fixed on testing stand, although structure is simple, it is possible to achieve reuse, cost-effective, but the pressure of system to be measured
The parameter such as power, temperature needs additionally to increase the sensor such as pressure, temperature and relevant measurement pipeline and circuit, therefore increases
The complexity of test bay system, and influence whether the security reliability of whole system, and then affect electromotor combustion oil system
Performance test.At present, data of literatures is not also had to do Xiang the modular device of collection measurement, collection, communication and fast connection function
Real introduction and be available for referring to, the research connect intelligence soon the most still belongs to blank.If Aero Engine Testing system uses logical
Quick access device, from device reasonability, safety, sealing and structure function, there is also a lot of deficiency, can't be
Big probability ground meets Aero Engine Testing and connects requirement soon.
Summary of the invention
It is an object of the invention to provide a kind of aero-engine combustion oil system assay device, existing device can be substituted,
Overcome traditional testing equipment deficiency functionally, guarantee test equipment connect soon safe and reliable, convenient connect soon while, can be straight
Connect monitoring the combustion temperature of oil system, pressure and other parameters, and at the aspect such as safety, sealing, there is good performance, preferably real
The intellectuality of existing quick access device, completes to meet the requirement that Aero Engine Testing quickly connects.
The concrete scheme of the present invention is: aero-engine combustion oil system assay device includes connecting interface and control system,
Being provided with pressure and temp composite module arranged in pairs on described connection interface, every pair of pressure and temp composite module is respectively by pressure
Power thermomechanical interface is connected stand with aero-engine combustion oil system and test-bed and connects, and connects interface and is additionally provided with power supply
System, the network interface being connected with central workbench；Control system includes master control circuit board and is arranged in master control circuit board
Signal input output interface, power supply interface, supply module, communication module, central processing unit, conditioning module, described power supply
Interface is connected with the electric power system being connected on interface by signal shielding cable, and connects master control by supply module and power supply circuits
Circuit board processed, powers for connecting each electronic component of interface and control system, and signal input output interface passes through signal shielding cable
Connect with the network interface being connected on interface, and be connected with master control circuit board with communicating circuit by communication module, every pair of pressure
The pressure and temp electric interfaces of temperature composite module is connected with conditioning module by signal shielding cable, and by conditioning module and tune
Reason circuit is connected with master control circuit board, and master control circuit board is connected with central processing unit by central control circuit, it is achieved signal
Real-time communication.Described pressure and temp composite module includes pressure transducer and conditioning plate, temperature sensor and conditioning plate, root
The scope measured according to aero-engine combustion lubricating oil, arranges multiple pressure transducer and temperature sensor, is such as provided with four to eight
Individual, it is each two pressure transducers of 10Mpa, 1Mpa, 0.1Mpa, 0.01Mpa and eight temperature including the pressure range measured
Tolerance journey is the temperature sensor of 0～230 DEG C.Described power supply circuits, communicating circuit and central control circuit are arranged on master control
On circuit board.
Assay device of the present invention is fixed on stand, by establishment control program, through central control circuit and central workstation
Carry out data transmission；Controlled the sequence of acquisition performance parameter by test instruction, after central processing unit processes, test is joined
Number is transferred to the central workstation of master control system, and feedback test parameter signal state.Connect the pressure and temp module tool on interface
There is multiple range, in concrete process of the test, correspond to different ranges, select accordingly, carry out aviation and send out
The test of motivation combustion oil system.The present invention need not increase extra pipeline and circuit, overcomes traditional testing equipment function
On deficiency, guarantee test equipment connect soon safe and reliable, convenient connect soon while, can directly monitor the temperature of combustion oil system
Degree, pressure and other parameters, and at the aspect such as safety, sealing, there is good performance, preferably achieve the intelligence of quick access device
Change, complete to meet the requirement that Aero Engine Testing quickly connects.
Accompanying drawing explanation
Fig. 1 is the attachment structure schematic diagram of the present invention.
Detailed description of the invention
As it can be seen, aero-engine combustion oil system assay device includes connecting interface I and control system II, described
It is provided with pressure and temp composite module 1a arranged in pairs, every couple of pressure and temp composite module 1a on connection interface I to pass through respectively
Pressure and temp mechanical interface 1b is connected stand IV connects with aero-engine combustion oil system III and test-bed, connects interface also
It is provided with electric power system 1c, the network interface 1d being connected with central workbench；Control system II includes master control circuit board 2 He
Be arranged on signal input output interface 2a in master control circuit board, power supply interface 2b, supply module 2c, communication module 2e, in
Central processor 2f, conditioning module 2g, described power supply interface 2b passes through signal shielding cable and the power supply system being connected on interface I
System 1c connects, and connects master control circuit board 2 by supply module 2c and power supply circuits, for connecting interface I and control system
Each electronic component of II is powered, and signal input output interface 2a passes through signal shielding cable and the network interface being connected on interface I
1d connects, and is connected with master control circuit board 2 with communicating circuit by communication module 2e, every couple of pressure and temp composite module 1a
Pressure and temp electric interfaces 1f be connected with conditioning module 2g by signal shielding cable, and pass through conditioning module 2g and conditioning
Circuit is connected with master control circuit board 2, and master control circuit board 2 is connected with central processing unit 2f by central control circuit, real
The real-time communication of existing signal.Described pressure and temp composite module 1a include pressure transducer and conditioning plate, temperature sensor and
Conditioning plate, the scope measured according to aero-engine combustion lubricating oil, arrange multiple pressure transducer and temperature sensor, such as arrange
Have four to eight, be each two pressure transducers of 10Mpa, 1Mpa, 0.1Mpa, 0.01Mpa including the pressure range measured
With the temperature sensor that eight temperature ranges are 0～230 DEG C.Described power supply circuits, communicating circuit and central control circuit set
Put on main control board 2.
In work, aero-engine combustion oil system assay device is while completing to connect soon with electromotor combustion lubricating oil, the completeest
Become aero-engine the combustion pressure of oil system, the connection work of temperature channel.During test, control system is by connecting on interface
Electric power system, power supply circuits power, control program write central processing unit, central workstation and assay device carry out data biography
Defeated, utility control program simultaneously, by the digital quantity in signal input output interface real time scan pressure and temp composite module, and
Perform central workstation and the instruction of central processing unit, carry out real-time status transmission with central workstation, complete aero-engine combustion
The pressure of oil system, temperature parameter are measured, it is achieved the combustion collection of oil system performance parameter, process, complete central authorities' work simultaneously
Make the station storage of real-time performance parameter, analytic function；And Real-time Feedback pressure and temperature parameter state, it is achieved aero-engine is fired
The test of oil system.
Claims (4)
1. an aero-engine combustion oil system assay device, is characterized in that, described device includes connecting interface (I) and controlling
System (II), described connection interface (I) is provided with pressure and temp composite module (1a) arranged in pairs, every pair of pressure and temp
Composite module (1a) is connected with aero-engine combustion oil system (III) and test-bed by pressure and temp mechanical interface (1b) respectively
Stand (IV) connects, and connects interface and is additionally provided with electric power system (1c), the network interface (1d) being connected with central workbench；Control
System processed (II) includes master control circuit board (2) and the signal input output interface (2a) being arranged in master control circuit board, power supply
Interface (2b), supply module (2c), communication module (2e), central processing unit (2f), conditioning module (2g), described power supply connects
Mouth (2b) is connected by signal shielding cable and the electric power system (1c) being connected on interface (I), and by supply module (2c) and confession
Electricity circuit connects master control circuit board (2), powers for connecting each electronic component of interface (I) and control system (II), and signal is defeated
Enter output interface (2a) to be connected with the network interface (1d) being connected on interface (I) by signal shielding cable, and pass through communication module
(2e) it is connected with master control circuit board (2) with communicating circuit, the pressure and temp electric interfaces of every pair of pressure and temp composite module (1a)
(1f) it is connected with conditioning module (2g) by signal shielding cable, and by conditioning module (2g) and modulate circuit and main control circuit
Plate (2) is connected, and master control circuit board (2) is connected with central processing unit (2f) by central control circuit, it is achieved leading in real time of signal
News.
2. aero-engine combustion oil system assay device as claimed in claim 1, is characterized in that, described pressure and temp group
Compound module (1a) includes pressure transducer and conditioning plate, temperature sensor and conditioning plate, measures according to aero-engine combustion lubricating oil
Scope, arrange multiple pressure transducer and temperature sensor.
3. aero-engine combustion oil system assay device as claimed in claim 2, is characterized in that, described pressure transducer
Be provided with four to eight with temperature sensor, including the pressure range measured be 10Mpa, 1Mpa, 0.1Mpa,
Each two pressure transducers of 0.01Mpa and eight temperature ranges are the temperature sensor of 0～230 DEG C.
4. aero-engine combustion oil system assay device as claimed in claim 1, is characterized in that, described power supply circuits,
Communicating circuit and central control circuit are arranged in master control circuit board (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410568092.3A CN104330262B (en) | 2014-10-23 | 2014-10-23 | Aero-engine combustion oil system assay device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410568092.3A CN104330262B (en) | 2014-10-23 | 2014-10-23 | Aero-engine combustion oil system assay device |
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| CN104330262A CN104330262A (en) | 2015-02-04 |
| CN104330262B true CN104330262B (en) | 2016-09-28 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181337B (en) * | 2015-05-25 | 2018-01-05 | 北京航天三发高科技有限公司 | Test bay engine fuel system and its application method |
| CN105223893A (en) * | 2015-11-02 | 2016-01-06 | 沈阳航天新光集团有限公司 | Aeromotor ground stand trystate supervisory system |
| CN105675322A (en) * | 2016-01-13 | 2016-06-15 | 中国航空动力机械研究所 | Lubricating oil tank performance test system and method |
| CN114486276A (en) * | 2021-12-29 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Turboprop aircraft outer lubricating oil system and engine ground rack joint test device |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3960011A (en) * | 1974-11-18 | 1976-06-01 | Harris Corporation | First fault indicator for engines |
| US5198980A (en) * | 1990-11-05 | 1993-03-30 | Patrick James D | Portable testing apparatus for airplane engines |
| CN201071514Y (en) * | 2007-09-10 | 2008-06-11 | 黄河勘测规划设计有限公司工程物探研究院 | Integrated test analyzer for groundwork |
| CN101231215A (en) * | 2008-02-28 | 2008-07-30 | 北京航空航天大学 | Device and method for testing upper air performance of aircraft engine fuel oil system |
| CN201732013U (en) * | 2010-08-03 | 2011-02-02 | 无锡威锐科智能测控技术有限公司 | Control device for performance testing of CVT valve body |
| CN102353542A (en) * | 2011-09-28 | 2012-02-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Lubricant pump testing device for automatically measuring flow of aeroengine and control method thereof |
| CN103062155A (en) * | 2012-12-19 | 2013-04-24 | 天津工程机械研究院 | Modularization hydraulic comprehensive testing system and testing method thereof |
| CN203490512U (en) * | 2013-08-31 | 2014-03-19 | 中国煤炭科工集团太原研究院 | Measurement and control system for performance test of mining explosion-proof diesel engine |
| CN203572657U (en) * | 2013-10-30 | 2014-04-30 | 中国南方航空工业(集团)有限公司 | Parameter measuring device of internal fuel oil pipeline system of aero-engine |
| CN204165752U (en) * | 2014-10-23 | 2015-02-18 | 哈尔滨东安发动机（集团）有限公司 | Aeromotor combustion oil system test unit |
-
2014
- 2014-10-23 CN CN201410568092.3A patent/CN104330262B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3960011A (en) * | 1974-11-18 | 1976-06-01 | Harris Corporation | First fault indicator for engines |
| US5198980A (en) * | 1990-11-05 | 1993-03-30 | Patrick James D | Portable testing apparatus for airplane engines |
| CN201071514Y (en) * | 2007-09-10 | 2008-06-11 | 黄河勘测规划设计有限公司工程物探研究院 | Integrated test analyzer for groundwork |
| CN101231215A (en) * | 2008-02-28 | 2008-07-30 | 北京航空航天大学 | Device and method for testing upper air performance of aircraft engine fuel oil system |
| CN201732013U (en) * | 2010-08-03 | 2011-02-02 | 无锡威锐科智能测控技术有限公司 | Control device for performance testing of CVT valve body |
| CN102353542A (en) * | 2011-09-28 | 2012-02-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Lubricant pump testing device for automatically measuring flow of aeroengine and control method thereof |
| CN103062155A (en) * | 2012-12-19 | 2013-04-24 | 天津工程机械研究院 | Modularization hydraulic comprehensive testing system and testing method thereof |
| CN203490512U (en) * | 2013-08-31 | 2014-03-19 | 中国煤炭科工集团太原研究院 | Measurement and control system for performance test of mining explosion-proof diesel engine |
| CN203572657U (en) * | 2013-10-30 | 2014-04-30 | 中国南方航空工业(集团)有限公司 | Parameter measuring device of internal fuel oil pipeline system of aero-engine |
| CN204165752U (en) * | 2014-10-23 | 2015-02-18 | 哈尔滨东安发动机（集团）有限公司 | Aeromotor combustion oil system test unit |
Non-Patent Citations (1)
| Title |
|---|
| 某型航空发动机滑油系统试验台计算机控制系统设计与实现;杨帆;《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》;20040915(第3期);第C031-161页 * |
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