CN110044634A - A kind of micro turbojet engine state and performance monitor apparatus - Google Patents
A kind of micro turbojet engine state and performance monitor apparatus Download PDFInfo
- Publication number
- CN110044634A CN110044634A CN201910258609.1A CN201910258609A CN110044634A CN 110044634 A CN110044634 A CN 110044634A CN 201910258609 A CN201910258609 A CN 201910258609A CN 110044634 A CN110044634 A CN 110044634A
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- engine
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- performance monitor
- monitor apparatus
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- 230000005540 biological transmission Effects 0.000 claims abstract description 15
- 239000007858 starting material Substances 0.000 claims abstract description 9
- 238000004891 communication Methods 0.000 claims abstract description 5
- 238000012545 processing Methods 0.000 claims description 16
- 238000001514 detection method Methods 0.000 claims description 7
- 230000005611 electricity Effects 0.000 claims description 3
- 241000208340 Araliaceae Species 0.000 claims description 2
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 claims description 2
- 235000003140 Panax quinquefolius Nutrition 0.000 claims description 2
- 235000008434 ginseng Nutrition 0.000 claims description 2
- 230000008450 motivation Effects 0.000 claims 1
- 238000012423 maintenance Methods 0.000 abstract description 8
- 238000012544 monitoring process Methods 0.000 abstract description 5
- 238000010248 power generation Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004806 packaging method and process Methods 0.000 description 2
- 230000036961 partial effect Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The invention discloses a kind of micro turbojet engine state and performance monitor apparatus, including remote platform, telecommunication unit for transmitting data to remote platform and receiving platform instructs, for receiving to instruct and pass to the control unit of associated execution unit, driving unit for acquiring engine data and being sent to the engine data acquisition transmission unit of associated control element and exported for starter/generator switching with power generation, remote platform and telecommunication unit are wirelessly connected, telecommunication unit, engine data acquires transmission unit, driving unit is electrically connected with control unit.By configuring a series of sensors and communication module when micro turbojet engine is in design, according to actual service condition, the time of monitoring arrangement oneself judgement replacement components, and predict engine failure position and fault time, failure rate when engine uses can be effectively reduced, flight safety is improved, and maintenance, upkeep cost is greatly reduced.
Description
Technical field
The present invention relates to aero-engine field, in particular to a kind of micro turbojet engine state and performance monitoring fill
It sets.
Background technique
The operating status of micro turbojet engine is directly related to the safety of aircraft.
Micro turbojet engine keeps the performance and stability of engine using the method that periodic maintenance is maintained at present.
It sends engine back to manufacturer at the appointed time and replaces corresponding components.
The excessive maintenance of engine is caused in this way, is transported, and packaging, with high costs, operating time shortens, so that one
The preferable component of partial properties is scrapped, and causes greatly to waste.And it can not thoroughly solve engine health and stabilization
The problem of, unpredictable engine is when, what components will appear failure, whether can not detect components in operation
The state of maintenance, replacement is arrived.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of micro turbojet engine state and performance monitor apparatus, purports
It in the excessive maintenance for solving one side engine, transports, packaging, with high costs, operating time shortens, so that a part of
The component of better performances is scrapped, and causes the problem of greatly wasting；On the other hand engine health cannot thoroughly be solved
With stable problem, when is unpredictable engine, what components will appear failure, can not detect zero in operation
Whether part has arrived the problem of state of maintenance, replacement.
In order to solve the above-mentioned technical problem, the technical solution of the present invention is as follows:
A kind of micro turbojet engine state and performance monitor apparatus, including remote platform, for being passed to remote platform
The telecommunication unit that send data and receiving platform to instruct, for receiving instruction and passing to the control list of associated execution unit
Member acquires transmission unit and for starting for acquiring engine data and being sent to the engine data of associated control element
The driving unit of motor switching and power generation output, the remote platform and the telecommunication unit are wirelessly connected, described long-range
Communication unit, engine data acquisition transmission unit, driving unit are electrically connected with described control unit.
Preferably, the remote platform includes receiver and data processing unit, and the receiver is for receiving engine
Acquire the data that transmission unit is sent, the number that the data processing unit is received for data processing and analysis comparison receiver
According to the receiver and the data processing unit are electrically connected.
Preferably, the engine data acquisition transmission unit includes sensor board, and the sensor board includes at least 3 tunnels
Temperature detection route, at least 2 tunnel pressure detecting routes, at least 2 road current vortex sensor routes, Rotating speed measring route and voltage
With current sense link.
Preferably, the driving unit includes driving oil pump, driving igniter processed, switching starter/generator, driving main oil pipe
Solenoid valve, drive ignition oil pipe solenoid valve.
Preferably, the telecommunication unit includes bluetooth and GPRS module, and the bluetooth is for connecting display with mobile phone
Engine behavior and adjusting parameter, the telecommunication unit are uploaded to remote platform engine by the GPRS module
Detection parameters.
By adopting the above technical scheme, by increasing a series of sensors and communication module on micro turbojet engine,
In use according to the actual use situation and current real-time status of each component of engine, monitoring arrangement oneself judgement replacement
Failure rate when engine uses can be effectively reduced in the time of components, and prediction engine failure position and fault time,
Flight safety is improved, and maintenance, upkeep cost is greatly reduced.Currently, software upgrading needs to send engine back to life in engine
Business men carries out, and after the system, engine can not have to remove aircraft, directly be upgraded by remote platform, greatly
Saved upgrade cost, extend the up time of engine.
Detailed description of the invention
Fig. 1 is the structural block diagram of micro turbojet engine state and performance monitor apparatus provided by the invention；
Fig. 2 is the ECU schematic diagram of micro turbojet engine state provided by the invention and performance monitor apparatus.
In figure, 1- engine, 2- engine data acquires transmission unit, and 3- control unit, 4- driving unit, 5- remotely puts down
Platform, 6- telecommunication unit, 7- igniting oil pipe solenoid valve, 8- main oil pipe solenoid valve, 9- starter/generator, 10- igniter, 11- oil
Pump.
Specific embodiment
Specific embodiments of the present invention will be further explained with reference to the accompanying drawing.It should be noted that for
The explanation of these embodiments is used to help understand the present invention, but and does not constitute a limitation of the invention.In addition, disclosed below
The each embodiment of the present invention involved in technical characteristic can be combined with each other as long as they do not conflict with each other.
As shown in Figure 1, a kind of micro turbojet engine state and performance monitor apparatus, including remote platform 5, for
Remote platform 1 transmits data and the telecommunication unit 6 that receiving platform instruct, for receiving instruction and passing to related to execute list
The control unit 3 of member acquires transmission unit 2 for acquiring engine data and being sent to the engine data of associated control element
And switch the driving unit 4 with the output that generates electricity, the remote platform 5 and 6 nothing of telecommunication unit for starter/generator
Line connection, the telecommunication unit 6, engine data acquisition transmission unit 2, driving unit 4 are electric with described control unit 3
Property connection.
Preferably, the remote platform 5 includes receiver and data processing unit, and the receiver is for receiving engine
Acquire the data that transmission unit 2 is sent, the number that the data processing unit is received for data processing and analysis comparison receiver
According to the receiver and the data processing unit are electrically connected.
Preferably, the engine data acquisition transmission unit 2 includes sensor board, and the sensor board includes at least three
Road temperature detection route, at least two-way pressure detecting route, at least two-way current vortex sensor route, Rotating speed measring route and
Voltage and current sense link.
As shown in Fig. 2, in the present embodiment, being provided with three tunnel temperature detection routes, two-way pressure detecting on the engine
Route, two-way current vortex sensor route, 1 Rotating speed measring route of engine, and to the voltage and current sense link of battery,
The parameter of above-mentioned wireline inspection is sent to control unit 3 and passes through telecommunication simultaneously by engine data acquisition transmission unit 2
Unit 6 sends receiver to, is transferred to data processing unit by receiver, data processing unit compares the data of acquisition
Analysis judges replacement components according to the actual use situation of each component of engine 1 and current real-time status come system oneself
Time, and prediction 1 abort situation of engine and fault time, control unit 3 control driving unit 4 according to the case where detection,
Instruction of the driving unit 4 according to control unit 3, driving oil pump 11, drive ignition device 10, switching starter/generator 9, driving main oil pipe
Solenoid valve 8, drive ignition oil pipe solenoid valve 7.Driving unit 4 can not only switch starter/generator to be exported with power generation, but also right
Sensor board charge and discharge control.Wherein, telecommunication unit 6 includes bluetooth and GPRS module, and bluetooth is aobvious for connecting with mobile phone
Show engine behavior and adjusting parameter, telecommunication unit 6 is uploaded to 5 engine 1 of remote platform by GPRS module and examines
Survey parameter.
Working principle: by the way that temperature sensor, pressure sensor, current vortex sensor, revolving speed on the engine is arranged
The parameter of sensor, voltage and the current detecting acquisition each key component of engine 1, by telecommunication unit 6 and remote platform 5
Connection, transmits these parameters to remote platform 5.Remote platform 5 utilizes data processing unit according to the data that receiver receives
Analysis comparison is done, each component of engine 1 and overall performance state value are finally provided, thus the operation of monitor engines in real time 1
State.The service life for being detected components is predicted by data processing unit.Meanwhile the software systems run in engine 1
System upgrade can be carried out by remote platform.It 3 real time inspection operational data of control unit and modifies and various starts and runs ginseng
Number, instruction of the driving unit 4 according to control unit 3, driving oil pump 11, drive ignition device 10, switching starter/generator 9, driving master
Oil pipe solenoid valve 8, drive ignition oil pipe solenoid valve 7.
Using technical solution of the present invention, by increasing a series of sensors and communication mould on micro turbojet engine
Block, in use according to the actual use situation and current real-time status of each component of engine 1, monitoring arrangement oneself judgement
The time of components, and prediction 1 abort situation of engine and fault time are replaced, when the use of engine 1 can be effectively reduced
Failure rate improves flight safety, and maintenance, upkeep cost is greatly reduced.Currently, software upgrading needs will start in engine 1
Machine 1 sends manufacturer back to carry out, and after the monitoring arrangement, engine 1 can not have to remove aircraft, directly passes through remote platform
5 are upgraded, and upgrade cost has greatly been saved, and extend the up time of engine 1.
In conjunction with attached drawing, the embodiments of the present invention are described in detail above, but the present invention is not limited to described implementations
Mode.For a person skilled in the art, in the case where not departing from the principle of the invention and spirit, to these embodiments
A variety of change, modification, replacement and modification are carried out, are still fallen in protection scope of the present invention.
Claims (5)
1. a kind of micro turbojet engine state and performance monitor apparatus, it is characterised in that: including remote platform, be used for remote
Cheng Pingtai transmits the telecommunication unit of data and receiving platform instruction, for receiving to instruct and passing to associated execution unit
Control unit acquires transmission unit and use for acquiring engine data and being sent to the engine data of associated control element
Switch the driving unit with the output that generates electricity in starter/generator, the remote platform and the telecommunication unit are wirelessly connected, institute
Telecommunication unit, engine data acquisition transmission unit, driving unit is stated to be electrically connected with described control unit.
2. micro turbojet engine state according to claim 1 and performance monitor apparatus, it is characterised in that: described remote
Cheng Pingtai includes receiver and data processing unit, and the receiver is used to receive the number that engine acquisition transmission unit is sent
According to the data processing unit compares the data that receiver receives, the receiver and the number for data processing and analysis
It is electrically connected according to processing unit.
3. micro turbojet engine state according to claim 1 and performance monitor apparatus, it is characterised in that: the hair
Motivation data acquisition and sending unit includes sensor board, and the sensor board includes at least 3 tunnel temperature detection routes, at least 2 tunnels
Pressure detecting route, at least 2 road current vortex sensor routes, Rotating speed measring route and voltage and current sense link.
4. micro turbojet engine state according to claim 1 and performance monitor apparatus, it is characterised in that: the drive
Moving cell includes driving oil pump, driving igniter processed, switching starter/generator, driving main oil pipe solenoid valve, drive ignition oil pipe electricity
Magnet valve.
5. micro turbojet engine state according to claim 1 and performance monitor apparatus, it is characterised in that: described remote
Journey communication unit includes bluetooth and GPRS module, and the bluetooth is for connecting display engine behavior and adjustment ginseng with mobile phone
Number, the telecommunication unit are uploaded to remote platform engine detection parameters by the GPRS module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910258609.1A CN110044634A (en) | 2019-04-01 | 2019-04-01 | A kind of micro turbojet engine state and performance monitor apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910258609.1A CN110044634A (en) | 2019-04-01 | 2019-04-01 | A kind of micro turbojet engine state and performance monitor apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110044634A true CN110044634A (en) | 2019-07-23 |
Family
ID=67275841
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910258609.1A Pending CN110044634A (en) | 2019-04-01 | 2019-04-01 | A kind of micro turbojet engine state and performance monitor apparatus |
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| CN (1) | CN110044634A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050017876A1 (en) * | 2003-07-23 | 2005-01-27 | Harris Corporation | Wireless engine monitoring system |
| CN201044050Y (en) * | 2007-04-25 | 2008-04-02 | 韩晓明 | Electronic control engine remote monitoring system |
| CN201096016Y (en) * | 2007-11-14 | 2008-08-06 | 施远强 | Engines monitoring instrument |
| CN103728965A (en) * | 2012-10-15 | 2014-04-16 | 中航商用航空发动机有限责任公司 | Monitoring device and method for aircraft engine and FADEC system |
| CN204856109U (en) * | 2015-06-27 | 2015-12-09 | 朱新贺 | Thruster operation wireless monitoring system device |
| 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 |
| CN106706321A (en) * | 2015-11-18 | 2017-05-24 | 重庆市彭敏科技有限责任公司 | Engine unit monitoring system |
| CN107870598A (en) * | 2017-12-25 | 2018-04-03 | 董竞仪 | A kind of engine operation remote monitoring timing and current operating conditions judgment means and method |
-
2019
- 2019-04-01 CN CN201910258609.1A patent/CN110044634A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050017876A1 (en) * | 2003-07-23 | 2005-01-27 | Harris Corporation | Wireless engine monitoring system |
| CN201044050Y (en) * | 2007-04-25 | 2008-04-02 | 韩晓明 | Electronic control engine remote monitoring system |
| CN201096016Y (en) * | 2007-11-14 | 2008-08-06 | 施远强 | Engines monitoring instrument |
| CN103728965A (en) * | 2012-10-15 | 2014-04-16 | 中航商用航空发动机有限责任公司 | Monitoring device and method for aircraft engine and FADEC system |
| CN204856109U (en) * | 2015-06-27 | 2015-12-09 | 朱新贺 | Thruster operation wireless monitoring system device |
| 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 |
| CN106706321A (en) * | 2015-11-18 | 2017-05-24 | 重庆市彭敏科技有限责任公司 | Engine unit monitoring system |
| CN107870598A (en) * | 2017-12-25 | 2018-04-03 | 董竞仪 | A kind of engine operation remote monitoring timing and current operating conditions judgment means and method |
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| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190723 |