CN109406114A - A kind of aeroengine rotor blade working condition checkout gear and detection method - Google Patents
A kind of aeroengine rotor blade working condition checkout gear and detection method Download PDFInfo
- Publication number
- CN109406114A CN109406114A CN201710319806.0A CN201710319806A CN109406114A CN 109406114 A CN109406114 A CN 109406114A CN 201710319806 A CN201710319806 A CN 201710319806A CN 109406114 A CN109406114 A CN 109406114A
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- rotor blade
- aeroengine rotor
- working condition
- blade
- sensor
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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
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention provides a kind of aeroengine rotor blade working condition checkout gear and detection method based on MEMS technology, wherein device includes MEMS sensor and permanent magnet, the MEMS sensor is arranged in the tip of aeroengine rotor blade, the MEMS sensor includes that wireless communication chips, battery pack, control chip, induction coil and sensor, the permanent magnet are arranged at the position perpendicular on casing and with the induction coil.The present invention can obtain the gap data between vane tip and casing in real time, engine control system is provided and carries out tip clearance active control, record blade individualized work time history data, the health management system arranged carry out life-span management of blade is provided, the random vibration signal data during the h type engine h blade working are recorded, provide support for similar model blade construction Intensity Design.
Description
Technical field
The present invention relates to observation and control technology fields, fill more particularly to a kind of aeroengine rotor blade working state-detection
It sets and detection method.
Background technique
Aero-engine is aircraft major impetus device, and structure feature is as shown in figure 4, mainly by rotatable parts, such as wind
Fan a, compressor blade b, c, stator part, such as casing d composition.When aero-engine works, fan/compressor blade high speed
Rotation, needs to bear biggish centrifugal load, airload and vibrational loading, in addition, with the metal object of air-flow sucking, sand
The foreign objects such as stone, hail will also result in damage.Under the coupling of complicated stress field and random, accidental impairment factor, fan/
The accidents such as fatigue, fracture easily occur for compressor blade, seriously threaten flight safety.Therefore, in fan/compressor blade construction
Design phase needs as true as possible data to carry out all kinds of intensity evaluations and structure optimization, in addition, in fan/calm the anger
Health control is carried out during the usage of machine blade, if it is possible to the detailed carrying course that obtain blade, then in R & D design rank
Section can carry out careful design to leaf longevity.But above-mentioned load belongs to unstable state, random load more, and different leaves it
Between the load-time history that bears it is not exactly the same, it is big accurately to obtain data difficulty.
Technology and rests on model analysis, genetic algorithm, mind mainly for the identification of fan blade derogatory behaviour at present
Research through network scheduling theory basis.With the fast development of electronic technology, computer technology, network technology, material technology etc.,
Aviation observation and control technology has been greatly developed, and key technology mainly includes that intelligence and network sensor technology, structural health are examined
Survey and health control technology and Smart Structure Teehnology etc., such as:
Modal analysis technique.During generating damage and damage propatagtion using inside configuration, the inherent characteristic of structure can become
The characteristics of change, such as structural natural frequency reduces and the structural modal vibration shape changes, by testing, comparing damage front and back modal parameter
Variable quantity characterize structural damage degree.
Engine dynamic testing technology.For obtain blade working when stress-time data, in laboratory conditions, by
Engine fan/compressor blade some regions install sensor and pass through foil gauge in ground environment Imitating engine condition
The loaded data of blade different parts are acquired, foil gauge is connected on feed-through collar, and subsequent data are passed in acquisition equipment, warp
It is converted to the data such as the frequency of blade vibration after processing, and then analyzes blade vibration state.
Structural health detects (SHM) and health control technology.Prognostic and health management refer to using existing knowledge come
It predicts the health status in aircraft components future, comprehensive, accurately and real-time progress fault diagnosis and prediction can be compared, be conducive to
It reduces life cycle cost, ensure Flight Safety.Structural health detection technique mainly detects structural loads, is damaging
Hurt early period of origination and find damage, structural health detection system mainly includes four parts: sensing system, data acquisition, place
Reason and Transmission system, non-destructive tests, Modifying model, safety evaluation and early warning system.If U.S. NASA is by fiber optic sensor network
It is embedded to carbon fibre composite aircraft skin, makes material that there is perception and judgment.
Smart Structure Teehnology.Be sensor, driver, microcontroller and related circuit etc. is integrated in the structure, make this
Structure not only has the function of traditional receiving load, holding shape etc., also has identification, analysis, processing and self adaptive control etc.
Function makes its own or its local environment be in optimum state.Smart Structure Teehnology possible application in aircraft at present is main
Including smart skins, damage check intelligence structure, intensity and form adaptive intelligence structure and vibration and noise reducing intelligence structure.
The prior art has following deficiency:
1) be unable to real-time detection blade state, cause to control effectively to engine behavior, as blade tip with
Gap between casing is that one of the principal element of influence engine efficiency is needed especially for fan and high-pressure compressor
By tip clearance control in the range of a very little, it can only be adjusted at present by experience, be easy to happen blade and casing
Between touch mill.
2) oscillating load-time history data of blade cannot be acquired, it is difficult to effectively carry out blade health control, Bu Nengwei
Similar model fan/compressor blade provides data supporting.
3) in engine dynamic test, need to install foil gauge and this kind of experiment on blade usually in ground experiment room
Under the conditions of carry out, need to carry out biggish transformation to engine structure, to place test device, testing expense is high, the period is long,
Difficulty is big；The aerodynamic configuration of blade will be destroyed in blade surface installation sensor, influences pneumatic efficiency；Under ground experiment room environmental
The operating condition of blade is difficult to consistent with outfield service condition, and Ground Test Time is limited, these factors will lead to survey
Try data error.
Summary of the invention
The aeroengine rotor blade working condition checkout gear and inspection that the present invention provides a kind of based on MEMS technology
Survey method can obtain the gap data between vane tip and casing in real time, provide engine control system carry out blade tip between
Gap active control records blade individualized work time history data, provides blade health management system arranged carry out life-span management, remembers
The random vibration signal data during the h type engine h blade working are recorded, provide branch for similar model blade construction Intensity Design
Support.
The present invention provides a kind of aeroengine rotor blade working condition checkout gears, comprising: MEMS sensor and
Permanent magnet, the MEMS sensor are arranged in the tip of aeroengine rotor blade, and the MEMS sensor includes wireless
Communication chip, battery pack, control chip, induction coil and sensor, the permanent magnet be arranged on casing and with the induction
At the perpendicular position of coil.
Further, the battery pack is rechargeable battery pack.
Further, the sensor includes acceleration transducer and range sensor.
Further, the aeroengine rotor blade working condition checkout gear further includes reception of wireless signals
Device, the wireless signal receiver are arranged on casing.
The present invention also provides a kind of aeroengine rotor blade working condition detection methods, comprising: MEMS sensor
In response to the engine start moment, by the operating state data of sensor acquisition aeroengine rotor blade, and will collect
The operating state data of aeroengine rotor blade radio in the computer in cockpit；Calculating in cockpit
Operating state data of the machine to the aeroengine rotor blade of acquisition, the work shape of analysis acquisition aeroengine rotor blade
State information；The work state information for the aeroengine rotor blade that computer in cockpit is obtained according to analysis, determines boat
Whether the working condition of empty engine rotor blade is normal, and not just in response to the working condition of aeroengine rotor blade
Often, adjustment engine behavior is to avoid accident generation.
Further, the MEMS sensor, when the engine is working, by the permanent magnet on induction coil cutting casing
The electric energy power supply that magnetic field generates, and charge to battery pack；When engine does not work, by battery-powered.
Further, the operating state data of the collected aeroengine rotor blade includes acceleration transducer
The blade vibration amount data of acquisition, the distance between the vane tip of range sensor acquisition and casing data.
Further, the work state information for the aeroengine rotor blade that the analysis obtains includes the vibration of blade
Speed displacement information and the distance between vane tip and casing information.
Sensor is implanted into aeroengine rotor blade by the present invention, acceleration, blade tip during detection blade working
Spacing between casing, it is whether normal based on collected data judging blade working state, it avoids that accident occurs.Progress point
It is as follows: first, it proposes a kind of aeroengine rotor blade with ego state sensing capability, realizes aeroengine rotor
The measurement of the working condition of blade and record, the detection of detection and blade and casing gap including blade vibration magnitude；Second,
It is proposed a kind of method of supplying power to of wireless MEMS sensor, the high speed rotation based on aeroengine rotor blade generates dynamic
It can, combine with magnetic induction principle self-powered, do not have to special be equipped with power battery, diminution MEMS component volume, so that leaf
Piece has the ability that works long hours.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Fig. 1 is a kind of structural representation of aeroengine rotor blade working condition checkout gear of the embodiment of the present invention
Figure；
Fig. 2 is the permanent magnet and wireless communication of a kind of aeroengine rotor blade working condition checkout gear of the embodiment of the present invention
Position view is arranged in number receiver；
Fig. 3 is a kind of flow chart of aeroengine rotor blade working condition detection method of the embodiment of the present invention；
Fig. 4 is engine interior structural schematic diagram in the prior art.
It is attached in the figure, it is marked as
1 MEMS sensor
2 wireless communication chips
3 battery packs
4 control chips
5 induction coils
6 sensors
7 permanent magnets
8 wireless signal receivers.
Specific embodiment
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to is used to explain the present invention, and is not considered as limiting the invention.
The present invention provides a kind of aeroengine rotor blade working condition checkout gears, as depicted in figs. 1 and 2, packet
Include: MEMS sensor 1 and permanent magnet 7, the MEMS sensor 1 is arranged in the tip of aeroengine rotor blade, described
MEMS sensor 1 includes wireless communication chips 2, battery pack 3, control chip 4, induction coil 5 and sensor 6, the permanent magnet 7
It is arranged at the position perpendicular on casing and with the induction coil 5.Preferably, the battery pack is rechargeable battery pack,
The sensor includes acceleration transducer and range sensor.As shown in Figure 1, blade passes through hair during blade processing
After base, upset, finish forge, finish-forging, by integrated wireless communications chip 2, battery pack 3, control chip 4, induction coil 5 and sensor 6
MEMS sensor 1 be mounted at the suitable position of vane tip, through connect and adaptability processing after obtain final shape.
In one embodiment of the invention, the aeroengine rotor blade working condition checkout gear further includes
Wireless signal receiver 8, the wireless signal receiver 8 are arranged on casing.
In a specific embodiment, the process of blade are as follows:
(1) by WIFI chip, 1000mah lithium battery, induction coil, acceleration transducer, control chip package to titanium alloy block
In, become a MEMS component；
(2) the precision forged blade blank by the way of die forging, and plane is processed at the blade tip position of blade blank, reach welding
Required state, by equipped with MEMS component titanium alloy block welding manner securely, be securely fixed in blade blank
Tip；
(3) excess stock is removed to final blade profile using adaptive machining method according to blade digital-to-analogue；
(4) in engine crankcase manufacturing process, groove is reserved at interval of certain distance on the inside of casing, permanent magnet blocks are buried
Enter in groove, permanent magnet can also continuously be placed, and encapsulate, pre-buried coil position is assisted in permanent magnet position and fan blade
With design, keep magnetic induction line vertical with the direction of sensor coil.
During the work time, the vibratory output signal of acceleration transducer acquisition blade, range sensor acquire vane tip
The distance between casing signal, by wireless signal transmission to cockpit computer control system, computer control system is logical
Analysis blade working status information is crossed, engine speed, casing gap are made before blade working state reaches critical state
Adjustment in real time.The magnetic line of force that the permanent magnet that induction coil is mounted in casing by cutting generates produces electricl energy, and provides MEMS biography
Each device work in sensor, and charge for battery pack, it is MEMS sensor by battery pack when engine is in dead ship condition
Power supply.It perceives whether blade remains static simultaneously, determines whether MEMS sensor needs to maintain lowest energy consumption state.
The present invention also provides a kind of aeroengine rotor blade working condition detection methods, as shown in Figure 3, comprising:
Step S10, MEMS sensor is in response to engine start, by the work shape of sensor acquisition aeroengine rotor blade
State data, and the operating state data of collected aeroengine rotor blade is radioed into the computer in cockpit
In；
Step S20, computer in cockpit obtain the operating state data of the aeroengine rotor blade of acquisition, analysis
The work state information of aeroengine rotor blade；
Step S30, the work state information for the aeroengine rotor blade that the computer in cockpit is obtained according to analysis, sentences
Whether the working condition for determining aeroengine rotor blade is normal, and not in response to the working condition of aeroengine rotor blade
Normally, the working condition of engine is adjusted.
Wherein, the MEMS sensor, when the engine is working, by the magnetic field of the permanent magnet on induction coil cutting casing
The electric energy of generation is powered, and is charged to battery pack；When engine does not work, by battery-powered.The collected aviation
The operating state data of engine rotor blade includes the blade vibration amount data of acceleration transducer acquisition, and range sensor is adopted
The distance between the vane tip of collection and casing data.The working condition letter for the aeroengine rotor blade that the analysis obtains
Breath includes the vibration velocity displacement information and the distance between vane tip and casing information of blade.
Sensor is implanted into aeroengine rotor blade by the present invention, acceleration, blade tip during detection blade working
Spacing between casing, it is whether normal based on collected data judging blade working state, it avoids that accident occurs.Progress point
It is as follows: first, it proposes a kind of aeroengine rotor blade with ego state sensing capability, realizes aeroengine rotor
The measurement of the working condition of blade and record, the detection of detection and blade and casing gap including blade vibration magnitude；Second,
It is proposed a kind of method of supplying power to of nearly passive MEMS sensor, the high speed rotation based on aeroengine rotor blade uses magnetic strength
Self-powered method is answered, does not have to special outfit battery, reduces MEMS component volume, so that blade has the energy that works long hours
Power.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art within the scope of the invention can be to above-mentioned
Embodiment is changed, modifies, replacement and variant.
Claims (8)
1. a kind of aeroengine rotor blade working condition checkout gear characterized by comprising
MEMS sensor and permanent magnet, the MEMS sensor is arranged in the tip of aeroengine rotor blade, described
MEMS sensor includes wireless communication chips, battery pack, control chip, induction coil and sensor, and the permanent magnet setting exists
On casing and with the induction coil at perpendicular position.
2. aeroengine rotor blade working condition checkout gear as described in claim 1, which is characterized in that the battery
Group is rechargeable battery pack.
3. aeroengine rotor blade working condition checkout gear as described in claim 1, which is characterized in that the sensing
Device includes acceleration transducer and range sensor.
4. aeroengine rotor blade working condition checkout gear as described in claim 1, which is characterized in that further include nothing
Line signal receiver, the wireless signal receiver are arranged on casing.
5. a kind of aeroengine rotor blade working condition detection method characterized by comprising
MEMS sensor is in response to the engine start moment, by the working condition number of sensor acquisition aeroengine rotor blade
According to, and the operating state data of collected aeroengine rotor blade is wirelessly transferred away, by wireless signal receiver
It receives, finally passes in the computer in cockpit；
Computer in cockpit obtains aeroplane engine to the operating state data of the aeroengine rotor blade of acquisition, analysis
The work state information of rotor blade；
The work state information for the aeroengine rotor blade that computer in cockpit is obtained according to analysis determines aviation hair
Whether the working condition of motivation rotor blade is normal, and in response to the working state abnormal of aeroengine rotor blade, adjusts
The working condition for motivation of haircuting.
6. aeroengine rotor blade working condition detection method as claimed in claim 5, which is characterized in that the MEMS
Sensor is powered, and to electricity when the engine is working by the electric energy that the magnetic field of the permanent magnet on induction coil cutting casing generates
The charging of pond group；When engine does not work, by battery-powered.
7. aeroengine rotor blade working condition detection method as claimed in claim 5, which is characterized in that the acquisition
To aeroengine rotor blade operating state data include acceleration transducer acquisition blade vibration amount data, distance
The distance between the vane tip of sensor acquisition and casing data.
8. aeroengine rotor blade working condition detection method as claimed in claim 7, which is characterized in that the analysis
The work state information of the aeroengine rotor blade of acquisition include blade vibration velocity displacement information and vane tip with
The distance between casing information.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710319806.0A CN109406114A (en) | 2017-05-09 | 2017-05-09 | A kind of aeroengine rotor blade working condition checkout gear and detection method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710319806.0A CN109406114A (en) | 2017-05-09 | 2017-05-09 | A kind of aeroengine rotor blade working condition checkout gear and detection method |
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| CN109406114A true CN109406114A (en) | 2019-03-01 |
Family
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| CN201710319806.0A Pending CN109406114A (en) | 2017-05-09 | 2017-05-09 | A kind of aeroengine rotor blade working condition checkout gear and detection method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111780977A (en) * | 2019-03-18 | 2020-10-16 | 中国航发商用航空发动机有限责任公司 | Blade scraping and grinding monitoring method and monitoring system |
| CN112357113A (en) * | 2020-09-30 | 2021-02-12 | 成都飞机工业（集团）有限责任公司 | Electric device for inspecting blades of aircraft engine and counting method thereof |
| CN114235572A (en) * | 2021-11-30 | 2022-03-25 | 中国航空综合技术研究所 | Structural damage evaluation method based on signal similarity |
| CN114942119A (en) * | 2022-04-21 | 2022-08-26 | 北京理工大学 | High temperature and high speed rotating impeller machinery transient flow field test system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101050712A (en) * | 2007-05-24 | 2007-10-10 | 岂兴明 | Positive control for aviation engine turbine blade-tip gap |
| US20080282770A1 (en) * | 2007-05-18 | 2008-11-20 | Siemens Power Generation, Inc. | MEMS emissions sensor system for a turbine engine |
| CN102175135A (en) * | 2011-01-26 | 2011-09-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Non-contact measuring method for leaf apex radial clearance of engine rotor |
| EP2549065A1 (en) * | 2011-07-18 | 2013-01-23 | General Electric Company | System and method for operating a turbine |
| CN103775139A (en) * | 2012-10-26 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Gap control system and method for turbine engine |
-
2017
- 2017-05-09 CN CN201710319806.0A patent/CN109406114A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080282770A1 (en) * | 2007-05-18 | 2008-11-20 | Siemens Power Generation, Inc. | MEMS emissions sensor system for a turbine engine |
| CN101050712A (en) * | 2007-05-24 | 2007-10-10 | 岂兴明 | Positive control for aviation engine turbine blade-tip gap |
| CN102175135A (en) * | 2011-01-26 | 2011-09-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Non-contact measuring method for leaf apex radial clearance of engine rotor |
| EP2549065A1 (en) * | 2011-07-18 | 2013-01-23 | General Electric Company | System and method for operating a turbine |
| CN103775139A (en) * | 2012-10-26 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Gap control system and method for turbine engine |
Non-Patent Citations (2)
| Title |
|---|
| 闫晓军 等: "MEMS技术在智能航空发动机中的应用研究现状及前景", 《航空动力学报》 * |
| 陈璞: "基于MEMS技术的微型电源的研究", 《中国优秀硕士学位论文全文数据库 信息科技辑》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111780977A (en) * | 2019-03-18 | 2020-10-16 | 中国航发商用航空发动机有限责任公司 | Blade scraping and grinding monitoring method and monitoring system |
| CN111780977B (en) * | 2019-03-18 | 2022-03-11 | 中国航发商用航空发动机有限责任公司 | Blade scraping and grinding monitoring method and monitoring system |
| CN112357113A (en) * | 2020-09-30 | 2021-02-12 | 成都飞机工业（集团）有限责任公司 | Electric device for inspecting blades of aircraft engine and counting method thereof |
| CN114235572A (en) * | 2021-11-30 | 2022-03-25 | 中国航空综合技术研究所 | Structural damage evaluation method based on signal similarity |
| CN114235572B (en) * | 2021-11-30 | 2023-11-07 | 中国航空综合技术研究所 | Structural damage evaluation method based on signal similarity |
| CN114942119A (en) * | 2022-04-21 | 2022-08-26 | 北京理工大学 | High temperature and high speed rotating impeller machinery transient flow field test system |
| CN114942119B (en) * | 2022-04-21 | 2023-10-03 | 北京理工大学 | High-temperature high-speed rotating impeller machinery transient flow field test system |
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Application publication date: 20190301 |