CN103775212A - Fan failure braking device of aero-engine - Google Patents
Fan failure braking device of aero-engine Download PDFInfo
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- CN103775212A CN103775212A CN201210413857.7A CN201210413857A CN103775212A CN 103775212 A CN103775212 A CN 103775212A CN 201210413857 A CN201210413857 A CN 201210413857A CN 103775212 A CN103775212 A CN 103775212A
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- brake disc
- fan
- braking device
- fan shaft
- rotor brake
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Abstract
A fan failure braking device of an aero-engine comprises a fan shaft, a fan blade, a bearing support piece and a bearing component, wherein a rotor brake disc is arranged on the fan shaft; the fan blade is mounted on the fan shaft; one end of the bearing support piece is mounted on an aero-engine casing, the bearing support piece is provided with a stator brake disc which circumferentially surrounds the rotor brake disc and is radially spaced from the rotor brake disc; one end of the bearing component is coupled with the other end of the fan shaft, and connected with the bearing support piece by a predetermined bending moment; when the fan blade fractures, the fan shaft deflects outwards, so that when the mutation bending moment between the bearing component and the bearing support piece exceeds the predetermined bending moment, the bearing component and the bearing support piece are disconnected, and thus the rotor brake disc and the stator brake disc are jointed. when the fan blade fails and fractures, rub-impact occurs between the rotor brake disc and the stator brake disc, limits the radial displacement of bending of the fan shaft and reduces the rotational speed of the fan shaft and the FBO (Fan Blade Out) load.
Description
Technical field
The present invention relates to a kind of fan fails braking device of aeroengine.
Background technique
In the middle of Aeroengine Design, containment regulation that must be by seaworthiness, the most harsh condition is when fan blade occurs coming off, motor can contain blade breakage, and still need to continue running more than 3 hours with windmill rotating speed after killing engine.Fan blade (the FBO that comes off, Fan Blade Out) time, engine running is at higher rotating speed, the radially unbalanced load (FBO load) producing is very large, reaches tens tons, and radially unbalanced load passes to bearing support structure by bearing, be delivered to afterwards intermediary's casing, pass to aircraft by joint system is installed again, if require motor to bear FBO load completely, the structural strength of motor is proposed to very high requirement.
The method of tradition reply FBO load is to adopt larger design safety factor, strengthen the intensity of motor, as strengthen bearings intensity, strengthen intermediary casing intensity, strengthen installing the intensity of joint etc., and such design increases the weight of motor greatly, particularly in modern civil aviation, will affect the fuel economy of motor, it is on a sticky wicket in fierce market competition.
Summary of the invention
First object of the present invention is can reduce FBO load in the time that motor generation fan blade comes off.
Second object of the present invention is to improve Security, makes motor design lighter structure by less safety coefficient, to obtain better fuel economy.
The 3rd object of the present invention is to make when reducing FBO load the destructiveness of engine structure to be down to lower degree.
Device disclosed in this invention, has the maximum radial displacement of limiting engine bending shaft generation and the effect of deflection angle.Under FBO load, bearing supports and clutch shaft bearing assembly disconnect, and then after engine axis bending, rotor brake disc and stator brake disc as braking device touch mill, retraining in the radial direction the free beat of fan shaft, limit the maximum deflection angle of fan shaft, can reduce like this bending load producing in the second bearing unit and other structures.The maximum radial displacement of fan blade and maximum radial displacement and the deflection angle of deflection angle and fan shaft are basically identical; within being limited in maximum license radial displacement; can prevent that fan blade and casing from producing compared with large collision and gross distortion and clamping stagnation; thereby prevent very big moment of torsion; and then protection fan shaft structure, also can prevent that multiple blades from again rupturing and increasing unbalanced load.
On the other hand, the present invention has the effect that reduces FBO load.Rotor brake disc and stator brake disc touch after mill, produce certain frictional force, and bearing support structure on fan shaft, reduces rapidly the rotating speed of fan shaft Braking.Square being directly proportional of radially unbalanced load on fan shaft and its rotating speed, the reduction of rotating speed has reduced the unbalanced load of fan shaft.
Fan blade comes off moment, the destruction maximum that engine structure is produced, when having passed through dangerous spot, the rotating speed of fan shaft reduces greatly, the degree of crook of fan shaft is corresponding reducing also, rotor brake disc and the stator brake disc of braking device are thrown off, no longer produce surface friction drag, now motor enters windmill condition and smooth running.
Particularly, the invention discloses a kind of fan fails braking device of aeroengine, it comprises: fan shaft, is provided with rotor brake disc on it; Fan blade, it is arranged on described fan shaft, and the relatively described rotor brake disc of described fan blade is positioned at upstream on fluid flow direction; Bearing supports, its one end is arranged on casing, and described bearing supports is provided with stator brake disc, and described stator brake disc is circumferentially around described rotor brake disc radially spaced apart with described rotor brake disc; Bearing unit, its one end is couple to the other end on described fan shaft and is connected on described bearing supports with predetermined moment of flexure; Wherein, in the time of described fan blade fracture, when described fan shaft makes Breaking bending moment between described bearing unit and described bearing supports exceed described predetermined moment of flexure to extrinsic deflection, thereby described bearing unit and described bearing supports depart from and are connected described rotor brake disc and engage with described stator brake disc.
Preferably, described stator brake disc is fixed block, when rotor brake disc moves radially, is no more than stator brake disc position.
Preferably, the outer side surface of described rotor brake disc is rubbing surface, and the inner side surface of stator brake disc is rubbing surface.
More preferably, on described rubbing surface, comprise projection, indenture or the decorative pattern for increasing frictional force.
Preferably, described bearing unit is connected with overload inefficacy part with described bearing supports, as shear pin or shearing bolt.
Preferably, described bearing support also relatively described bearing unit be couple on described fan shaft with another bearing unit in the downstream of described fluid flow direction.
Preferably, described rotor brake disc adopts such as pin or tongue-and-groove or the outstanding structure of profile of tooth and is fixedly attached on described fan shaft.
Preferably, described bearing unit comprise outer race assembly, bearing inner ring assembly and be arranged in rotationally described outer race assembly and described bearing inner ring assembly between bearing roller, wherein, described bearing inner ring assembly is connected on described fan shaft, and described outer race assembly is connected on described bearing supports.
Preferably, the front end of described rotor brake disc is in abutting connection with described bearing roller, and described fan shaft is also provided with the nut for compress described rotor brake disc in the contrary direction of described fluid flow direction in the rear end in abutting connection with described rotor brake disc.
Preferably, described stator brake disc itself is one, or described stator brake disc and described bearing supports are one.
Beneficial effect of the present invention is as follows:
Under FBO load, rotor brake disc and stator brake disc bump, maximum radial displacement and the deflection angle of fan shaft are limited, reduce on the one hand the flexural load at the second bearing and other structure places, can prevent that on the other hand fan blade and casing from producing compared with large collision and gross distortion and clamping stagnation, produce very big moment of torsion, destroy fan shaft structure, or multiple blade again ruptures and increases unbalanced load.
When FBO initially occurs, between rotor brake disc and stator brake disc rubbing surface, produce larger braking force, fan propeller rotating speed is reduced rapidly, make unbalanced load under FBO state reduce rapidly (unbalanced load roughly to square being directly proportional of fan shaft rotating speed).
After fan shaft rotating speed reduces greatly, rotor brake disc and stator brake disc are thrown off, and no longer produce braking force, and aeroengine enters windmill condition continuous running smoothly.
Accompanying drawing explanation
In order to explain the present invention, its illustrative embodiments will be described with reference to the drawings hereinafter, in accompanying drawing:
Fig. 1 is the schematic diagram of the fan fails braking device of motor in the time of normal state;
Fig. 2 is the perspective view of rotor brake disc;
Fig. 3 is the schematic diagram that motor ruptures in fan blade fan fails braking device instantaneous;
Fig. 4 is motor enters the fan fails braking device of windmill condition schematic diagram in fan blade fracture;
Similar features in different figure is indicated by similar reference character.
Embodiment
As shown in Figure 1, it shows the schematic diagram of the fan fails braking device of motor in the time of normal operation.Particularly, this fan fails braking device mainly comprises: fan shaft 8, fan blade 10, bearing supports 3 and clutch shaft bearing assembly 16.Wherein, fan shaft 8 extends along engine axis 14, is provided with rotor brake disc 1 on it.Fan blade 10 is arranged on fan shaft 8, relative this rotor brake disc 1 of this fan blade 10 on fluid flow direction in upstream.Fan blade 10 is arranged on and in this fan blade 10, radially stretches out and held and protect by fancase 11.The rear end of bearing supports 3 is fixed on intermediary's casing 12, the front end stator brake disc 2 that extended internally, this stator brake disc 2 is circumferentially around this rotor brake disc 1 radially spaced apart with this rotor brake disc 1, and the inner side surface of stator brake disc 2 is used as rubbing surface.Clutch shaft bearing assembly 16 comprise ring member 7 in clutch shaft bearing outer ring assembly 5, clutch shaft bearing and be arranged in rotationally this clutch shaft bearing outer ring assembly 5 and clutch shaft bearing in clutch shaft bearing roller 6 between ring member 7, wherein, this clutch shaft bearing outer ring assembly 5 is fixedly connected with the front end of bearing supports 3 by shear pin 4, and in this clutch shaft bearing, ring member 7 is fixedly attached on this fan shaft 8.Shear pin 4 can bear the predetermined moment of flexure between bearing supports 3 and the clutch shaft bearing outer ring assembly 5 of clutch shaft bearing assembly 16, that is, within the scope of this predetermined moment of flexure, this shear pin 4 can not rupture, and will rupture once be greater than this shear pin 4 of this predetermined moment of flexure.Be appreciated that this shear pin 4 can be transshipped inefficacy part by other and replace, for example, can also use shearing bolt.The close rear end of this bearing supports 3 is also connected with the second bearing unit 17, this second bearing unit 17 comprises the second outer race assembly 18, the second bearing inner ring assembly 19 and is arranged in rotationally the second bearing roller 13 between this second outer race assembly 18 and the second bearing inner ring assembly 19, wherein, this the second outer race assembly 18 is fixedly connected with bearing supports 3, and this second interior ring member 19 is fixedly attached on this fan shaft 8.Bearing supports 3 is circumferentially fixed on intermediary's casing 12 and by clutch shaft bearing assembly 16 and the second bearing unit 17 and is radially supported on fan shaft 8.
As shown in Figure 2, it shows a kind of mode of execution of the rotor brake disc 1 of fan fails braking device of the present invention.Wherein, this rotor brake disc 1 is annular, and it has the outer side surface 300 as rubbing surface, can also be provided with projection, indenture or decorative pattern etc. for frictional force is increased on outer side surface 300.Multiple profile of tooth bumps 301 of also arranging equably on the internal surface of rotor brake disc 1, by these profile of tooth bumps 301, this rotor brake disc 1 can be connected on fan shaft 8, is appreciated that these profile of tooth bumps 301 can be replaced by the structure such as pin or tongue-and-groove.In addition, in the direction of engine axis 14, the front end of this rotor brake disc 1 is in abutting connection with clutch shaft bearing roller 6, and its rear end is compressed by nut 15.
Like this, when motor is during in normal state, fan shaft 8 and fan blade 10 are rotated around engine axis 14, and the moment of flexure that is delivered to shear pin 4 from fan blade 10 is no more than predetermined moment.
In the time there is fan blade fracture, as shown in Figure 3, the moment of flexure that is far longer than predetermined moment of flexure that huge unbalanced load produces is delivered to shear pin 4 makes shear pin 4 cut off inefficacy, bearing supports 3 loses radial support effect at front end, this moment of flexure must make the spin axis of fan shaft 8 bend, roughly from the rotating bending centered by engine axis 14 shown in Fig. 1 to the rotation centered by spin axis 100 shown in Fig. 3.The skew of the spin axis of fan blade causes rotor brake disc 1 position to be moved, rotor brake disc 1 touches mill with stator brake disc 2,, the outer friction surface 300 of rotor brake disc 1 and the collision of the internal surface of stator brake disc 2, this has reduced the striking force of fan blade 10 with fancase 11 greatly, prevent more than one blade damaged and continue increase load, on the other hand, the outer friction surface 300 of rotor brake disc 1 provides braking moment with the frictional force that the internal surface of stator brake disc 2 produces for fan shaft 8 slows down, and the rotating speed of fan shaft 8 is constantly reduced.
As shown in Figure 4, after fan shaft 8 rotating speeds reduce greatly, corresponding the reducing of moment of flexure that unbalanced force produces, fan shaft 8 is roughly got back to rotation centered by spin axis 200 from rotation centered by spin axis 100, and this spin axis 200 can be called the fan shaft spin axis of windmill condition.Now, rotor brake disc 1 is thrown off with stator brake disc 2, no longer produces braking force, and motor enters windmill condition continuous running smoothly.
Although in the above-described embodiment, this stator brake disc 2 and bearing supports 3 are made into integration, but those of ordinary skill in the art should be appreciated that this stator brake disc 2 also can be independent of this bearing supports 3 and manufacture separately.
Although those skilled in the art should be appreciated that having described rotor brake disc 1 is above connected on fan shaft 8 by its profile of tooth projection 301, but other the mode that is fixedly connected with is also fine.
Of the present invention produce effect as follows:
Under FBO load, bearing supports 3 and clutch shaft bearing assembly 16 disconnect, and then after engine axis bending, rotor brake disc 1 as braking device bumps with stator brake disc 2, the maximum radial displacement and the deflection angle that have limited the bending generation of fan shaft 8, can reduce the bending load producing in the second bearing unit and other structures like this.Maximum radial displacement and the deflection angle of the maximum radial displacement of fan blade 10 and deflection angle and fan shaft 8 are basically identical; within being limited in maximum license radial displacement; can prevent that fan blade 10 and casing 11 from producing compared with large collision and gross distortion and clamping stagnation; thereby prevent very big moment of torsion; and then protection fan shaft 8 structures, also can prevent that multiple blades from again rupturing and increasing unbalanced load.On the other hand, the present invention has the effect that reduces FBO load.Rotor brake disc and 1 stator brake disc 2 touch after mill, produce certain frictional force, and bearing support structure on fan shaft 8, reduces rapidly the rotating speed of fan shaft 8 Braking.Square being directly proportional of radially unbalanced load on fan shaft 8 and its rotating speed, the reduction of rotating speed has reduced the unbalanced load of fan shaft.
The present invention is limited to the illustrative embodiments presenting in specification and accompanying drawing never in any form.Within all combinations of the mode of execution (part) illustrating and describe are interpreted as clearly and are incorporated to this specification and be interpreted as and fall within the scope of the present invention clearly.And in the scope of the present invention of summarizing as claims, a lot of distortion are possible.In addition, any reference mark in claims should be configured to limit the scope of the invention.
Claims (10)
1. a fan fails braking device for aeroengine, it comprises:
Fan shaft, is provided with rotor brake disc on it;
Fan blade, it is arranged on described fan shaft, and the relatively described rotor brake disc of described fan blade is positioned at upstream on fluid flow direction;
Bearing supports, its one end is arranged on casing, and described bearing supports is provided with stator brake disc, and described stator brake disc is circumferentially around described rotor brake disc radially spaced apart with described rotor brake disc;
Bearing unit, its one end is couple to the other end on described fan shaft and is connected on described bearing supports with predetermined moment of flexure;
Wherein, in the time of described fan blade fracture, when described fan shaft makes Breaking bending moment between described bearing unit and described bearing supports exceed described predetermined moment of flexure to extrinsic deflection, thereby described bearing unit and described bearing supports depart from and are connected described rotor brake disc and engage with described stator brake disc.
2. fan fails braking device according to claim 1, is characterized in that, described stator brake disc is fixed block, when rotor brake disc moves radially, is no more than stator brake disc position.
3. fan fails braking device according to claim 1, is characterized in that, the outer side surface of described rotor brake disc is rubbing surface, and the inner side surface of stator brake disc is rubbing surface.
4. fan fails braking device according to claim 3, is characterized in that, comprises projection, indenture or decorative pattern for increasing frictional force on described rubbing surface.
5. fan fails braking device according to claim 1, is characterized in that, described bearing unit is connected with overload inefficacy part with described bearing supports, as shear pin or shearing bolt.
6. fan fails braking device according to claim 1, is characterized in that, described bearing support also relatively described bearing unit is couple on described fan shaft with another bearing unit in the downstream of described fluid flow direction.
7. fan fails braking device according to claim 1, is characterized in that, described rotor brake disc adopts such as pin or tongue-and-groove or the outstanding structure of profile of tooth and is fixedly attached on described fan shaft.
8. fan fails braking device according to claim 1, it is characterized in that, described bearing unit comprise outer race assembly, bearing inner ring assembly and be arranged in rotationally described outer race assembly and described bearing inner ring assembly between bearing roller, wherein, described bearing inner ring assembly is connected on described fan shaft, and described outer race assembly is connected on described bearing supports.
9. fan fails braking device according to claim 5, it is characterized in that, the front end of described rotor brake disc is in abutting connection with described bearing roller, and described fan shaft is also provided with the nut for compress described rotor brake disc in the contrary direction of described fluid flow direction in the rear end in abutting connection with described rotor brake disc.
10. according to the fan fails braking device described in claim 1-9 any one, it is characterized in that, described stator brake disc itself is one, or described stator brake disc and described bearing supports are one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210413857.7A CN103775212B (en) | 2012-10-25 | 2012-10-25 | A kind of fan fails brake unit of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210413857.7A CN103775212B (en) | 2012-10-25 | 2012-10-25 | A kind of fan fails brake unit of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103775212A true CN103775212A (en) | 2014-05-07 |
| CN103775212B CN103775212B (en) | 2016-11-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210413857.7A Active CN103775212B (en) | 2012-10-25 | 2012-10-25 | A kind of fan fails brake unit of aero-engine |
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| CN (1) | CN103775212B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105756723A (en) * | 2014-12-15 | 2016-07-13 | 中航商用航空发动机有限责任公司 | Device and method for active fusing, and aero-engine |
| CN107227980A (en) * | 2016-03-24 | 2017-10-03 | 中国航发商用航空发动机有限责任公司 | Automatically adjust the Aero-engine Bearing supporting structure of rigidity |
| WO2017166846A1 (en) * | 2016-03-28 | 2017-10-05 | 中国航发商用航空发动机有限责任公司 | Aero-engine and fusing method thereof under fan blade out load |
| CN107795384A (en) * | 2016-08-31 | 2018-03-13 | 中国航发商用航空发动机有限责任公司 | Disconnect device and aero-engine |
| CN110088427A (en) * | 2016-12-23 | 2019-08-02 | 赛峰飞机发动机公司 | Including the turbine for making the device of the de- connection of fan |
| CN113047959A (en) * | 2019-12-27 | 2021-06-29 | 中国航发商用航空发动机有限责任公司 | Aeroengine braking device and aeroengine |
| CN114526161A (en) * | 2022-04-22 | 2022-05-24 | 成都中科翼能科技有限公司 | Gas turbine's intermediary machine casket and reinforcement structure thereof |
Families Citing this family (1)
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| FR3129175B1 (en) * | 2021-11-15 | 2023-10-27 | Safran Aircraft Engines | TURBOMACHINE MODULE WITH AN AMPLITUDE LIMITING DEVICE AND CORRESPONDING TURBOMACHINE |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105756723A (en) * | 2014-12-15 | 2016-07-13 | 中航商用航空发动机有限责任公司 | Device and method for active fusing, and aero-engine |
| CN107227980A (en) * | 2016-03-24 | 2017-10-03 | 中国航发商用航空发动机有限责任公司 | Automatically adjust the Aero-engine Bearing supporting structure of rigidity |
| CN107227980B (en) * | 2016-03-24 | 2019-07-09 | 中国航发商用航空发动机有限责任公司 | Automatically adjust the Aero-engine Bearing supporting structure of rigidity |
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| CN110088427A (en) * | 2016-12-23 | 2019-08-02 | 赛峰飞机发动机公司 | Including the turbine for making the device of the de- connection of fan |
| CN110088427B (en) * | 2016-12-23 | 2022-02-18 | 赛峰飞机发动机公司 | Turbomachine comprising means for uncoupling a fan |
| CN113047959A (en) * | 2019-12-27 | 2021-06-29 | 中国航发商用航空发动机有限责任公司 | Aeroengine braking device and aeroengine |
| CN113047959B (en) * | 2019-12-27 | 2022-07-12 | 中国航发商用航空发动机有限责任公司 | Aeroengine braking device and aeroengine |
| CN114526161A (en) * | 2022-04-22 | 2022-05-24 | 成都中科翼能科技有限公司 | Gas turbine's intermediary machine casket and reinforcement structure thereof |
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| CN103775212B (en) | 2016-11-23 |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |