CN107227980A - Automatically adjust the Aero-engine Bearing supporting structure of rigidity - Google Patents
Automatically adjust the Aero-engine Bearing supporting structure of rigidity Download PDFInfo
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- CN107227980A CN107227980A CN201610171184.7A CN201610171184A CN107227980A CN 107227980 A CN107227980 A CN 107227980A CN 201610171184 A CN201610171184 A CN 201610171184A CN 107227980 A CN107227980 A CN 107227980A
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- supporting structure
- rigidity
- engine
- performs device
- sensor
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Wind Motors (AREA)
Abstract
The present invention provides a kind of Aero-engine Bearing supporting structure for automatically adjusting rigidity, and it includes supporting structure body, sensor, signal processing apparatus and performs device；Signal processing apparatus is used for after the monitoring signals processing by sensor and passes it to performs device；Sensor is used for the unbalanced load for monitoring engine, and monitoring variable is associated with the unbalanced load of engine, and when monitoring variable is less than predetermined threshold level, performs device keeps the rigidity of the predetermined position of supporting structure body to be in original state；When the monitoring variable of sensor is equal to or higher than predetermined threshold level, performs device reduces the rigidity of the predetermined position of supporting structure body immediately, to reduce the rigidity of supporting structure body, and when the monitoring variable of subsequent sensor is less than predetermined threshold level, the rigidity of the predetermined position of performs device increase supporting structure body, to improve the rigidity of supporting structure body.
Description
Technical field
The present invention relates to Aero-engine Bearing supporting structure.
Background technology
Birotor fanjet is a kind of aero-engine generally used on commercial aircraft, comprising high pressure rotor and
Low pressure rotor.In engine operation process, it may be made due to unavoidable causes such as foreign object suction, fatigues
There is larger unbalanced load in rotor-support-foundation system, causes the vibratory response of engine to be returned more than limits value, it is necessary to stop
Boat and maintenance.The support stiffness of regulation rotor-support-foundation system is the dynamics for changing rotor, reduction rotor oscillation response
Important measures.
By taking FBO events as an example, for ensure engine FBO events generation after can safe landing, typically from
The weak part of one mechanical performance (such as thinning section, fusing are set on the nearest bearing support cone wall of low pressure rotor
Pin etc.), it is failed under predetermined load (threshold value) effect.After generation FBO events, impaired starts
Chance is stopped immediately, engine from higher working speed be slowly drop down to windmill rotate during, bearing branch
Holding the weak position of mechanical performance on cone wall can fail.The support stiffness of bearing can so be reduced, make low pressure rotor
The critical speed reduction of system, unbalanced load reduces, to avoid occurring catastrophic failure.
However, the above-mentioned bearing support cone wall with fusing design all uses purely mechanic fusing mode, in imbalance
The lower fracture failure of load effect, can only unidirectionally reduce bearing stiffness, it is impossible to recover or increase the branch of bearing again
Hold rigidity, it is impossible to provide support stiffness again during subsequent flights.For example, in windmill rotational phase, it is necessary to
The critical speed that bearing provides support stiffness to ensure rotor is higher than windmill rotating speed.Now, if support stiffness is too small,
Cause the critical speed of rotor close to windmill rotating speed, engine can be caused persistently to bear larger in windmill rotational phase
Vibratory response, it is abnormally dangerous.
In summary, existing bearing support cone wall or rigidity can not be adjusted, or after can only mechanically fusing,
Rigidity can not be again provided during subsequent flights, it is therefore desirable to one kind can bidirectional modulation support stiffness, and can
The bearing support structure of recycling.
The content of the invention
It is an object of the invention to provide a kind of Aero-engine Bearing supporting structure for automatically adjusting rigidity.
A kind of Aero-engine Bearing supporting structure for automatically adjusting rigidity includes supporting structure body, sensor, letter
Number processing unit and performs device；The signal processing apparatus is used for after the monitoring signals processing by the sensor
And pass it to the performs device；The sensor is used for the unbalanced load for monitoring engine, the monitoring
Amount is associated with the unbalanced load of engine, when its monitoring variable is less than predetermined threshold level, and the performs device is kept
The rigidity of the predetermined position of the supporting structure body is in original state；The monitoring variable of the sensor is equal to or high
When predetermined threshold level, the performs device reduces the rigidity of the predetermined position of the supporting structure body immediately, with
Reduce the rigidity of the supporting structure body, and be less than the preset threshold in the monitoring variable of the subsequent sensor
During value, the performs device increases the rigidity of the predetermined position of the supporting structure body, is tied with improving the supporting
The rigidity of structure body.
In one embodiment, the shutdown phase after the generation of FBO events, the performs device reduces the supporting
The rigidity of the predetermined position of structural body, so that the critical speed of low pressure rotor is reduced to well below working speed, with
Reduce unbalanced load of the engine in docking process, it is described to perform dress when engine reaches windmill rotational phase
The rigidity for improving the supporting structure body is put, to increase the critical speed of low pressure rotor, it is turned far above windmill
Speed, to reduce being moved around rail for low pressure rotor, reduces the vibration of engine.
In one embodiment, it is described when the monitoring variable of the sensor reaches the amount after the unbalanced load disappearance
Performs device makes the rigidity of the predetermined position of the supporting structure body return to the original state.
In one embodiment, the sensor is foil gauge, vibrating sensor or acceleration transducer.
In one embodiment, the performs device be provided in the supporting structure body it is the predetermined position,
The mechanical structure either controllable intelligent material of rigidity can be changed by size of current.
In one embodiment, the performs device includes magnetic rheology elastic body and its magnet exciting coil.
In one embodiment, the sensor sets monitoring position on the engine that it is normally transported in engine
Monitoring variable is insensitive during row but occurs its monitoring variable significant changes after anomalous event.
In one embodiment, the Aero-engine Bearing supporting structure is the support cone arm of the bearing of low pressure rotor, institute
Stating support cone arm includes internal layer support cone arm and outer layer support cone arm, and the performs device is arranged on the outer layer supporting
Bore the predetermined position of arm.
The present invention due to by controllable performs device can after monitors load reaches predetermined threshold level immediately from
It is dynamic to change the rigidity of supporting structure, therefore help avoid the engine long time and bear unbalanced load.
Brief description of the drawings
The above and other features of the present invention, property and advantage are by by with reference to the accompanying drawings and examples
Describe and become readily apparent from, wherein：
Fig. 1 be one embodiment of the invention in automatically adjust rigidity Aero-engine Bearing supporting structure schematic diagram.
Embodiment
With reference to specific embodiments and the drawings, the invention will be further described, elaborates in the following description more
Many details are to facilitate a thorough understanding of the present invention, still the present invention obviously can be with a variety of different from the other of this description
Mode is implemented, and those skilled in the art can be in the case of without prejudice to intension of the present invention according to practical situations
Make similar popularization, deduction, therefore should not be limited the scope of the invention with the content of this specific embodiment.
It should be noted that these and follow-up other accompanying drawings are only as an example, it is not according to equal proportion
Condition draw, and should not be construed as limiting in this, as the protection domain to actual requirement of the present invention.
As shown in figure 1, automatically adjust rigidity Aero-engine Bearing supporting structure include supporting structure body,
Sensor 10, signal processing apparatus 12 and performs device 17.Supporting structure body includes internal layer support cone arm
7 and outer layer support cone arm 8.Signal processing apparatus 12 be used for by after the processing of the monitoring signals of sensor 10 and by its
Pass to performs device 17.Sensor 10 is used for the unbalanced load for monitoring engine, the monitoring variable and engine
Unbalanced load be associated, when monitoring variable be less than predetermined threshold level when, performs device 17 keep supporting structure sheet
The rigidity of the predetermined position of body is in original state, and such as performs device 17 may be at the state not being excited.
When the monitoring variable of sensor 10 is equal to or higher than predetermined threshold level, performs device 17 changes supporting structure sheet immediately
The rigidity of the predetermined position of body, to reduce the rigidity of this position of supporting structure, and in the prison of subsequent sensor 10
When measurement is less than predetermined threshold level, the rigidity of the predetermined position of the increase supporting structure body of performs device 17, to carry
The rigidity of high supporting structure body.
Performs device 17 can be provided in supporting structure body it is predetermined position, can be changed by size of current
The mechanical structure of rigidity either controllable intelligent material, or other any can change rigidity under signal control
Device.In Fig. 1, performs device 17 is arranged in outer layer support cone arm 8, is used as outer layer support cone arm 8
A part, the rigidity for changing outer layer support cone arm 8, and then change whole bearing support structure body
Rigidity.
After anomalous event generation, such as after the generation of FBO events, sensor 10 monitors that low pressure rotor is passed
The unbalanced load passed, the monitoring variable of sensor 10 will be above predetermined threshold level, and performs device 17 is according to sensing
The monitoring signals of device 10 change the rigidity of outer layer support cone arm 8 immediately, reduce the predetermined of whole supporting structure body
The rigidity at position.In subsequent shutdown phase, performs device 17 reduces the firm of the predetermined position of supporting structure body
Degree, so that the critical speed of low pressure rotor is reduced to well below working speed, to reduce engine in docking process
Unbalanced load.And when engine reaches windmill rotational phase, performs device 17 improves outer layer support cone arm
8 rigidity, to increase the critical speed of low pressure rotor, makes it be far above windmill rotating speed, to reduce low pressure rotor
Around rail motion, the vibration of engine is reduced.When the monitoring variable of sensor 10 reaches the amount after unbalanced load disappearance,
Performs device 17 makes the rigidity of outer layer support cone arm 8 return to original state, i.e., before the generation of FBO events
State.
In Fig. 1, engine configuration includes high and low pressure dual rotors system, and rotor bearing scheme therein is low
Rotor low pressure rotor is pressed to be supported by 1#, 2# and 5# bearing, wherein 2# bearings 6 are ball bearing, 1# bearings
5 and figure in the 5# bearings that are not shown be stick roller bearing.In the embodiment shown in fig. 1,1# bearing branch is adjusted
The bearing support structure that cone wall rigidity is held to reduce FBO load or other abnormal loads is illustrated.Wherein perform dress
The selection put can be diversified, is illustrated here with certain magnetic rheology elastic body device.Magnetic rheology elastic body it is firm
Degree performance can be controlled by externally-applied magnetic field, and good reversibility, removed after externally-applied magnetic field, restPosed again.
Performs device 17 includes magnet exciting coil 14 and magnetic rheology elastic body 15, and it is encapsulated by clamping plate 16a, 16b, magnetic
Magnetorheological elastomer 15 is set as a part for outer layer support cone arm 8.
Partial structurtes shown in Fig. 1 are the part-structure of the symmetrical low pressure rotor supporting structure of center line 1 vertically
Figure.In this embodiment, low pressure rotor 2 is supported jointly by 1# bearings 5 and 2# bearings 6, and low pressure rotor 2 is wrapped
Include fan, booster stage and low-pressure turbine etc..The support cone wall of 1# bearings 5 is double-decker, includes internal layer supporting
Bore wall 7 and outer layer support cone wall 8.In another embodiment, sent out according to the aviation for automatically adjusting rigidity of the present invention
Motivation bearing support structure can also be used for the situation that 1# bearing support cones wall is single layer structure.1# bearings 5 are by interior
Layer support cone wall 7 and the collective effect of outer layer support cone wall 8 are connected on stator casing 4.2# bearings 6 are by right
The support cone wall 9 answered is connected on stator casing 4.Outer layer supporting between 1# bearings 5 and stator casing 4
Predetermined performs device 17 is provided with cone wall 8.Sensor 10 is located near the bearing block of 1# bearings, is used for
The state of low pressure rotor is monitored, and monitoring signals are transferred to signal processing apparatus by monitoring signals transmission line 11
12.Signal processing apparatus 12 can be exported by performing signal transmssion line 13 according to the big minor adjustment of input signal
The size of electric current into magnet exciting coil 14, to change the rigidity of magnetic rheology elastic body 15, so as to adjust outer layer branch
The rigidity of cone wall 8 is held, it is final to change the support stiffness that 1# bearing support cone walls are supplied to low pressure rotor 2.
After FBO events occur, when the signal that sensor 10 is monitored is equal to or higher than predetermined threshold value, letter
Number processing unit 12 can reduce the electric current being input in magnet exciting coil 14, reduce the rigidity of magnetic rheology elastic body 15,
Make support stiffness reduction of the low pressure rotor 2 at 1# bearings 5, the critical speed of rotor is reduced to much smaller than work
Rotating speed, reduces unbalanced load.Hereafter, when engine reaches windmill rotating speed, the letter that sensor 10 is monitored
Number reduce, signal processing apparatus 12 can increase the electric current being input in magnet exciting coil 14, low pressure rotor 2 is existed
Support stiffness increase at 1# bearings 5, critical speed is increased to far above windmill rotating speed, reduced to a greater degree
The unbalanced load that engine is born.In summary, the support cone wall has bidirectional modulation support structure stiffness
Function, can reduce the imbalance in ramp to stop and windmill rotation process of the engine after the generation of FBO events
Load.
Signal processing apparatus 12 adjusts the electric current for being input to performs device 17, and the basis of magnetic rheology elastic body 15
The size of electric current is changed rigidity etc. and can realized using prior art in magnet exciting coil 14, is no longer described in detail herein.
In the aforementioned embodiment, sensor 10 can be foil gauge, vibrating sensor or acceleration transducer.Pass
The type of sensor 10 can not be limited, as long as the signal of engine abnormity event generation can be captured rapidly.
Performs device 17 is that stiffness tuning operation can have diversity, for example, controlled by the size of control electric current
The rigidity of mechanical structure, or by predetermined supporting portion using controllable intelligent material to change its rigidity, and
Other it is any can perform signal under control support structure stiffness device.
It is unwise that the monitoring position of sensor 10 on the engine is generally located in monitoring variable in normal engine operation
Sense, occurs after anomalous event, the monitoring variable significantly becomes big region.
Previous embodiment has following features：
1. by controllable performs device, supporting can be changed immediately after monitors load reaches predetermined threshold level
The rigidity of wall is bored, helping avoid the engine long time bears unbalanced load.
2. by the rigidity of the two-way change support cone wall of performs device, critical turn of low pressure rotor is reduced in shutdown phase
Speed, and critical rotor speed is improved in windmill rotational phase, can preferably it subtract for the different running statuses of engine
Small unbalanced load.
3. supporting structure need not be destroyed, the rigidity of supporting structure can be recovered after unbalanced load disappears, improved
Its service life.
4. by the rigidity of accurate adjustment bearing support cone wall, the design load of engine components system is reduced,
Help to reduce the design difficulty of engine.
Although the present invention is disclosed as above with preferred embodiment, it is not for limiting the present invention, any this area
Technical staff without departing from the spirit and scope of the present invention, can make possible variation and modification.Therefore,
Every content without departing from technical solution of the present invention, what the technical spirit according to the present invention was made to above example appoints
What modification, equivalent variations and modification, each falls within the protection domain that the claims in the present invention are defined.
Claims (8)
1. automatically adjust the Aero-engine Bearing supporting structure of rigidity, it is characterised in that including supporting structure body,
Sensor, signal processing apparatus and performs device；The signal processing apparatus is used for the monitoring of the sensor
After signal transacting and pass it to the performs device；The sensor is used for the uneven load for monitoring engine
Lotus, the monitoring variable is associated with the unbalanced load of engine, described when monitoring variable is less than predetermined threshold level
Performs device keeps the rigidity of the predetermined position of the supporting structure body to be in original state；The prison of the sensor
When measurement is equal to or higher than predetermined threshold level, the performs device reduces the reservations of the supporting structure body immediately
The rigidity of position, to reduce the rigidity of the supporting structure body, and is less than in the monitoring variable of the subsequent sensor
During the predetermined threshold level, the performs device increases the rigidity of the predetermined position of the supporting structure body, to carry
The rigidity of the high supporting structure body.
2. Aero-engine Bearing supporting structure as claimed in claim 1, it is characterised in that in FBO events
Shutdown phase after generation, the performs device reduces the rigidity of the supporting structure body, so that low pressure rotor
Critical speed is reduced to well below working speed, to reduce unbalanced load of the engine in docking process, works as hair
Motivation reaches windmill rotational phase, and the performs device improves the rigidity of the supporting structure body, to increase low pressure
The critical speed of rotor, makes it be far above windmill rotating speed, to reduce being moved around rail for low pressure rotor, reduces engine
Vibration.
3. Aero-engine Bearing supporting structure as claimed in claim 1, it is characterised in that the sensor
When monitoring variable reaches the amount after the unbalanced load disappearance, the performs device makes the pre- of the supporting structure body
The rigidity for determining position returns to the original state.
4. Aero-engine Bearing supporting structure as claimed in claim 1, it is characterised in that the sensor is
Foil gauge, vibrating sensor or acceleration transducer.
5. Aero-engine Bearing supporting structure as claimed in claim 1, it is characterised in that the performs device
It is provided in the machinery knot predetermined position, that rigidity can be changed by size of current of the supporting structure body
Structure either controllable intelligent material.
6. Aero-engine Bearing supporting structure as claimed in claim 1, it is characterised in that the performs device
Including magnetic rheology elastic body and its magnet exciting coil.
7. Aero-engine Bearing supporting structure as claimed in claim 1, it is characterised in that the sensor is set
Monitoring position on the engine is put so that its monitoring variable in normal engine operation is insensitive but generation is different
Its monitoring variable significant changes after ordinary affair part.
8. Aero-engine Bearing supporting structure as claimed in claim 1, it is characterised in that the aero-engine
Bearing support structure is the support cone arm of the bearing of low pressure rotor, and the support cone arm includes internal layer support cone arm and outer
Layer support cone arm, the performs device is arranged on the predetermined position of the outer layer support cone arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610171184.7A CN107227980B (en) | 2016-03-24 | 2016-03-24 | Automatically adjust the Aero-engine Bearing supporting structure of rigidity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610171184.7A CN107227980B (en) | 2016-03-24 | 2016-03-24 | Automatically adjust the Aero-engine Bearing supporting structure of rigidity |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107227980A true CN107227980A (en) | 2017-10-03 |
| CN107227980B CN107227980B (en) | 2019-07-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610171184.7A Active CN107227980B (en) | 2016-03-24 | 2016-03-24 | Automatically adjust the Aero-engine Bearing supporting structure of rigidity |
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| WO2020029716A1 (en) * | 2018-08-06 | 2020-02-13 | 中国航发商用航空发动机有限责任公司 | Load reduction apparatus for fan blade-out event of aero-engine |
| CN111412068A (en) * | 2020-03-27 | 2020-07-14 | 中国科学院工程热物理研究所 | Quick-response active control mechanism for rotor support rigidity |
| CN111894737A (en) * | 2019-05-05 | 2020-11-06 | 中国航发商用航空发动机有限责任公司 | Rotor support structure and gas turbine |
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| CN204140138U (en) * | 2014-09-25 | 2015-02-04 | 中航商用航空发动机有限责任公司 | A kind of engine rotor supporting structure and aeroengine |
| US20150098826A1 (en) * | 2012-04-25 | 2015-04-09 | General Electric Company | Apparatus and method for assembling a damper bearing assembly |
| WO2015105547A2 (en) * | 2013-11-26 | 2015-07-16 | United Technologies Corporation | Fan blade with segmented fan blade cover |
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| US20150098826A1 (en) * | 2012-04-25 | 2015-04-09 | General Electric Company | Apparatus and method for assembling a damper bearing assembly |
| CN103775212A (en) * | 2012-10-25 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Fan failure braking device of aero-engine |
| WO2015105547A2 (en) * | 2013-11-26 | 2015-07-16 | United Technologies Corporation | Fan blade with segmented fan blade cover |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020029716A1 (en) * | 2018-08-06 | 2020-02-13 | 中国航发商用航空发动机有限责任公司 | Load reduction apparatus for fan blade-out event of aero-engine |
| CN111894737A (en) * | 2019-05-05 | 2020-11-06 | 中国航发商用航空发动机有限责任公司 | Rotor support structure and gas turbine |
| CN111412068A (en) * | 2020-03-27 | 2020-07-14 | 中国科学院工程热物理研究所 | Quick-response active control mechanism for rotor support rigidity |
| CN111412068B (en) * | 2020-03-27 | 2021-02-12 | 中国科学院工程热物理研究所 | Quick-response active control mechanism for rotor support rigidity |
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| Publication number | Publication date |
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| CN107227980B (en) | 2019-07-09 |
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