CN203584480U - Turbine blade damping device and turbine thereof - Google Patents
Turbine blade damping device and turbine thereof Download PDFInfo
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- CN203584480U CN203584480U CN201320827740.3U CN201320827740U CN203584480U CN 203584480 U CN203584480 U CN 203584480U CN 201320827740 U CN201320827740 U CN 201320827740U CN 203584480 U CN203584480 U CN 203584480U
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- 238000013016 damping Methods 0.000 title claims abstract description 108
- 238000007789 sealing Methods 0.000 claims description 14
- 238000003466 welding Methods 0.000 claims description 3
- 238000006073 displacement reaction Methods 0.000 abstract description 4
- 238000005452 bending Methods 0.000 abstract description 3
- 230000002708 enhancing effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 9
- 238000000034 method Methods 0.000 description 8
- 230000001965 increasing effect Effects 0.000 description 7
- 230000005284 excitation Effects 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000000354 decomposition reaction Methods 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 210000003850 cellular structure Anatomy 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000000763 evoking effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000012761 high-performance material Substances 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
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Abstract
The utility model relates to a turbine blade damping device and a turbine thereof. The turbine blade damping device is positioned between a casing lining segment (1) and blades (4), and comprises at least one circle of damping rings (10) for damping, wherein the damping rings (10) are formed by connecting a plurality of fins (3) end to end. In the turbine blade damping device, fins are restrained by one another, the rigidity of the blades can be enhanced, the inherent frequencies of the blades can be changed and the bending and torsion stress of blade roots are reduced, thereby enhancing the resonance resistance and flutter resistance of the blades. When the blades vibrate, relative displacement is generated between fin pins and fin sleeves, thereby forming friction damping and absorbing the vibration energy of the blades.
Description
Technical field
The utility model relates to turbomachinery field, is specifically related to a kind of turbine blade damping device and comprises the turbine of this turbine blade damping device.
Background technique
Blade is the significant components in turbine, and it is generally subject to the effects such as alternate load of higher centrifugal load, aerodynamic loading and vibration at work, is easy to produce fault.According to statistics, in aeroengine, vibration fault rate accounts for the more than 60% of total failare rate in motor, and blade vibration rate of fault accounts for the more than 70% of vibration fault rate.The vibration fault of visible blade is problem comparatively serious in motor.
Aero gas turbine engine is all the time towards the future development of high thrust weight ratio, low-fuel-comsuption rate, long lifetime and high reliability, and the performance of modern aeroengine also improves along with fuel gas temperature and improving constantly of thrust weight ratio before pressure ratio, turbine.Therefore fan blade number and low-pressure turbine blade progression increase, and this has increased the possibility of resonance, and fan blade is also more and more longer with turbine blade simultaneously, and Oscillation Amplitude is increasing, very easily produce fatigue and rupture.
Aeroengine structural vibration has that it's too late feature can be divided into free vibration, forced vibration and self-excited vibration by excitation force.Free vibration refers to the simple harmonic oscillation that vibration system occurs under without alternation External Force Acting, and the natural frequency of vibration or natural frequency only depend on the physical parameter of vibration system.Forced vibration refer to that vibration system is carried outside periodicity alternation or displacement effect under the vibration that produces, it is evoked by extraneous excitation force, and with the frequency vibration of extraneous excitation force, when extraneous excitation force frequency is identical with vibration system, vibration system can produce strong resonance phenomenon.Self-excited vibration refers to the vibration that produced by self excitation force effect, by outer carrying periodically, do not caused, but the vibration of inducing because of former reason air-flows such as structure or operating conditions, blade flutter just belongs to typical self-excited vibration.
In order effectively to weaken the vibration of blade, avoid blade to resonate, eliminate the fault producing by vibrating, can set about from structural design and material selection two aspects of blade.Conventionally at blade unit, introduce certain structural type both at home and abroad, make blade there is vibration-damping function, and obtained good effect.The selecting of material is subject to the restriction of high performance material development.As present composite material wide-chord hollow fan blade, wide string design strengthens vane thickness, can reduce blade vibration stress, strengthen anti-foreign object and impact ability, the feature that composite material has has that quality is light, cost is low, the especially anti-Flutter Performance of resistance to shock is good, have good damage tolerance ability.
Press the position classification that vibration damping structure arranges, conventionally can be divided into blade root vibration damping and the large class of blade vibration damping two.According to the classification of blade damping approach, conventionally can be divided into two classes: a class is by increasing the damping of blade unit, reducing resonance amplitude and vibration stress, thereby improve the vibration resistance of blade; Another kind of is that material behavior or the situation of being heated, change Natural Frequency of Blade, reaches the object of blade vibration damping by changing the rigidity of blade.
In turbine development history, for what linear leaf before fan blade and gas compressor, for fear of blade resonance and flutter, improve anti-strike ability, on blade apart from blade root approximately 50%～70% place, a vibration damping convex shoulder (being commonly referred to damping platform) is set, and after having assembled, circumferentially the convex shoulder of blade forms a tubular, hold out against each other, strengthen rigidity, thereby change the natural frequency of blade, reduce blade root and reverse and flexural stress.
Vibration damping convex shoulder also can bring a lot of problems.Such as, vibration damping convex shoulder has reduced Flow area, and air mass flow is reduced; Vibration damping convex shoulder causes extra aerodynamic loss; Increased the weight of blade, blade root centrifugal stress strengthens, and convex shoulder and blade intersection produce flexural stress.
The problem of bringing in order to tackle vibration damping convex shoulder, some motors replace vibration damping convex shoulder in fan blade with shrouded blade, and this has reduced blade tip and has revealed loss, has improved aeroperformance, but the weight of blade tip significantly increased, and the centrifugal load of blade is larger.Its crown structure of shrouded blade is complicated, assembling difficulty, and according to statistics, integral shroud accounts for 10% of whole leaf weight, even higher.In engine operation process, because Shrouded turbine blade quality is large, blade working temperature is higher, and frequency is higher, is very easy to produce blade vibration fatigue damage fault.According to statistics, in the motor of being on active service, all once there is vibrating fatigue damage fault in various degree in nearly all gas compressor or turbine blade, wherein low-pressure turbine blade is motor one of the highest structure that breaks down, low-pressure turbine blade increases with engine performance and thrust weight ratio, load is increasing, blade is done thinner and thinner, rigidity worse and worse, this make low-pressure turbine blade resonance and Flutter Problem more and more outstanding.
Model utility content
The purpose of this utility model is to propose a kind of turbine blade damping device and turbine thereof, and this turbine blade damping device has solved the problems referred to above effectively.
For achieving the above object, the utility model provides following technological scheme:
A turbine blade damping device, turbine blade damping device, between casing lining section and blade, comprises that at least one circle is for the damping ring of vibration damping, damping ring is formed by a plurality of fin end-to-ends.
At one, preferably or alternatively in embodiment, each fin comprises fin pin and the fin cover that lays respectively at fin two ends, is that the fin cover that fin pin by a fin embeds another fin couples together between adjacent fins.
At one, preferably or alternatively in embodiment, each fin comprises the tip that is positioned at top, and turbine blade damping device also comprises the sealing layer that is positioned at damping ring outside, most advanced and sophisticatedly forms insert seal with sealing layer, and sealing layer is fixed on casing lining section inner side.
At one, preferably or alternatively in embodiment, between fin pin end face and fin cover end face, be provided with the spring for damping, spring is fixed on one of them end face.At one, preferably or alternatively in embodiment, fin pin outer surface is provided with the spring for damping.
At one preferably or alternatively in embodiment, in the outside of fin pin or the inner side of fin cover be provided with the wearing layer for damping.
At one preferably or alternatively in embodiment, the bottom surface of fin and the welding of the end face of blade or cast inblock.
At one preferably or alternatively in embodiment, a lining section direction from blade to casing, the cross section of fin reduces gradually.
At one, preferably or alternatively in embodiment, the bottom surface of a plurality of fins and the end face of individual blade weld respectively or cast inblock, and a plurality of fin end-to-ends form multi-turns for the damping ring of vibration damping.
The present invention also provides following technological scheme:
A turbine, turbine comprises turbine blade damping device as above.
Arbitrary technological scheme based in technique scheme, the utility model embodiment at least can produce following technique effect:
Because turbine blade damping device provided by the utility model is between casing lining section and blade, comprise that at least one circle is for the damping ring of vibration damping, damping ring is formed by a plurality of fin end-to-ends, fin restricts each other, can strengthen blade rigid, and can change the natural frequency of blade, reduce the bending and torsion stress of blade root, thereby improve anti-resonance vibration and the anti-flutter ability of blade; When blade produces vibration, between fin pin and fin cover, produce relative displacement, thereby form frictional damping, absorb the vibrational energy of blade; Fin is most advanced and sophisticated forms insert seal with sealing layer, thereby realize combustion gas, axially obturages, and reaches the object that reduces to reveal flow and reveal loss.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, forms the application's a part, and schematic description and description of the present utility model is used for explaining the utility model, does not form improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the assembling plan view that turbine blade damping device of the present utility model and casing serve as a contrast section, blade;
Fig. 2 is the decomposition plan view that turbine blade damping device of the present utility model and casing serve as a contrast section, blade;
Fig. 3 is the plan view that blade of the present utility model is connected with fin;
Fig. 4 is the decomposition side view that turbine blade damping device of the present utility model and casing serve as a contrast section, blade;
Fig. 5 is the assembling side elevation that turbine blade damping device of the present utility model and casing serve as a contrast section, blade;
Fig. 6 is the front assembled view that turbine blade damping device of the present utility model and casing serve as a contrast section, blade;
Fig. 7 is the assembling plan view that turbine blade damping device of the present utility model and casing serve as a contrast section, blade;
Fig. 8 is the assembling left view that turbine blade damping device of the present utility model and casing serve as a contrast section, blade;
Fig. 9 is the structural drawing of the damping ring being circumferentially connected to form by fin of the present utility model;
Figure 10 is the plan view that the blade of of the present utility model pair of rib tip structure is connected with fin;
Figure 11 has the assembling left view of shock-absorbing spring between fin pin end face of the present utility model and fin cover end face;
Figure 12 has the assembling right elevation of shock-absorbing spring between fin pin end face of the present utility model and fin cover end face;
Figure 13 is the assembling left view that fin pin outer surface of the present utility model is installed shock-absorbing spring;
Figure 14 is the assembling right elevation that fin pin outer surface of the present utility model is installed shock-absorbing spring.
Embodiment
Below by drawings and Examples, the technical solution of the utility model is described in further detail.
It should be noted that: any technical characteristics in the present embodiment, any technological scheme is all the technical characteristics of plurality of optional or one or more in optional technological scheme, cannot exhaustive all alternative technical characteristicss of the present utility model and alternative technological scheme in order to describe succinct need in presents, also the mode of execution that is not easy to each technical characteristics all emphasizes that it is one of optional numerous embodiments, so those skilled in the art should know: any technical characteristics in the present embodiment and any technological scheme all do not limit protection domain of the present utility model, protection domain of the present utility model should comprise that those skilled in the art do not pay the thinkable any alternate embodiments of creative work.
Below in order to narrate conveniently, hereinafter alleged " left side ", " right side ", " on ", left and right, the upper and lower of D score and accompanying drawing itself is to consistent.
As shown in Fig. 1-14, a kind of turbine blade damping device, turbine blade damping device, between casing lining section 1 and blade 4, comprises that at least one circle is for the damping ring 10 of vibration damping, damping ring 10 is formed by a plurality of fin 3 end-to-ends.
At least one circle refers to that for the damping ring of vibration damping damping ring can be a circle, also can be multi-turn, for example when damping ring is a circle, the bottom surface of a fin is connected on the end face of a blade, a plurality of fin end-to-end forms a circle for the damping ring of vibration damping, when damping ring is three circles, the bottom surface of three fins is connected on the end face of a blade, a plurality of fin end-to-end forms three circles for the damping rings of vibration damping.
Fin can be arranged at the blade tip of compressor blade or turbine blade, for obturaging and weakening blade vibration.The blade tip of individual blade is provided with a damping fin, and the fin on circumferencial direction connects and coordinates an annulus of formation.By increasing damping fin at blade tip, thereby change the damping of blade assembly, reach the object that increases blade vibration decrement.The every vibration one-period of blade, damping ring just consumes certain energy, and damping is larger, and energy consumption is just larger, and blade amplitude and vibration stress will reduce, and even play the effect that stops vibration, have guaranteed Security, reliability and the high-performance of blade.
Survey data shows, engine weight is as alleviated 17%, and the direct operating cost of aircarrier aircraft will decline 1%, and this will be that an airplane is saved 200,000 dollars in 1 year.The integral shroud of fin replace complex or damping boss structure, fin structure is simple, and weight is less than integral shroud, damping boss, analyzes and to show that the gross weight that fin accounts for blade is no more than 4%, and integral shroud can significantly reduce the weight of motor relatively.
Each fin 3 comprises and lays respectively at the fin pin 8 at fin 3 two ends and fin cover 9, is that the fin cover that fin pin by a fin embeds another fin couples together between adjacent fins.When blade produces vibration, between fin pin and fin cover, produce relative displacement, thereby form frictional damping, absorb the vibrational energy of blade; Fin restricts each other, can weaken the rigidity of blade and associate member system, changes the natural frequency of blade, reduces the bending and torsion stress of blade root, thereby improves anti-resonance vibration and the anti-flutter ability of blade.
Each fin 3 comprises the tip 7 that is positioned at top, and turbine blade damping device also comprises the sealing layer 2 that is positioned at damping ring outside, and most advanced and sophisticated 7 form insert seal with sealing layer 2, and sealing layer 2 is fixed on casing lining section 1 inner side.
Fin replaces complicated integral shroud, and its fin is most advanced and sophisticated forms insert seal with sealing layer, thereby realize combustion gas, axially obturages, and reaches the object that reduces to reveal flow and reveal loss.
Between fin pin end face 12 and fin cover end face 13, be provided with the spring 11 for damping, spring 11 is fixed on one of them end face, and for example 11, spring is fixed on fin pin end face 12 or 11, spring is fixed on fin cover end face 13.
Fin pin outer surface 14 is provided with the spring 11 for damping.
When vibration occurs blade, fin pin end face and fin overlap between end face or fin pin outer surface passes through spring vibration absorbing vibrational energy, play the effect of damping vibration attenuation.
In the outside of fin pin 8 or the inner side of fin cover 9 be provided with the wearing layer (not shown) for damping, the joint of fin pin 8 and fin cover 9 is by wearing layer vibration damping.When vibration occurs blade, the effect of damping vibration attenuation, by the wearing layer absorbing vibrational energy that rubs mutually, is played in joint.
Preferably, the length of fin pin 8 is less than the length of fin cover 9.
End face welding or the cast inblock of the bottom surface of fin 3 and blade 4.
The bottom surface 6 of a plurality of fins 3 and the end face of individual blade 4 weld respectively or cast inblock, and a plurality of fin 3 end-to-ends form multi-turn for the damping ring 10 of vibration damping.
As shown in figure 10, the blade 4 of two rib tip structures is connected with fin 3, and fin can combine with blade tip rib, and damping ring can be applied to the blade of blade tip rib structure.
A turbine, turbine comprises turbine blade damping device as above.
The other parts of turbine can be with reference to prior art, and the present invention no longer launches to describe.
Above-mentioned arbitrary technological scheme disclosed in the utility model unless otherwise stated, if it discloses number range, so disclosed number range is preferred number range, any it should be appreciated by those skilled in the art: preferred number range is only the obvious or representative numerical value of technique effect in many enforceable numerical value.Because numerical value is more, cannot be exhaustive, so the utility model just discloses part numerical value to illustrate the technical solution of the utility model, and the above-mentioned numerical value of enumerating should not form the restriction of the utility model being created to protection domain.
Simultaneously, if above-mentioned the utility model discloses or has related to component or the structural member of connection fastened to each other, so, unless otherwise stated, be fixedly connected with and can be understood as: can dismantle and be fixedly connected with (for example using bolt or screw to connect), also can be understood as: non-removable being fixedly connected with (for example rivet, weld), certainly, connection fastened to each other also can for example, be replaced (obviously cannot adopt except integrally formed technique) by integral type structure (use casting technique is integrally formed to be created).
In addition, in the disclosed arbitrary technological scheme of above-mentioned the utility model applied for the term that represents position relationship or shape unless otherwise stated its implication comprise and its approximate, similar or approaching state or shape.Arbitrary parts that the utility model provides can be both to be assembled by a plurality of independent constituent elements, the produced separate part of the technique that also can be one of the forming.
Finally should be noted that: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although the utility model is had been described in detail with reference to preferred embodiment, those of ordinary skill in the field are to be understood that: still can modify or part technical characteristics is equal to replacement embodiment of the present utility model; And not departing from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technological scheme scope that the utility model asks for protection.
Claims (10)
1. a turbine blade damping device, it is characterized in that, described turbine blade damping device is positioned between casing lining section (1) and blade (4), comprises that at least one circle is for the damping ring (10) of vibration damping, and described damping ring (10) is formed by a plurality of fins (3) end-to-end.
2. turbine blade damping device according to claim 1, it is characterized in that, described each fin (3) comprises fin pin (8) and the fin cover (9) that lays respectively at fin (3) two ends, is that the fin cover that fin pin by a fin embeds another fin couples together between adjacent fins.
3. turbine blade damping device according to claim 2, it is characterized in that, described each fin (3) comprises the tip (7) that is positioned at top, described turbine blade damping device also comprises the sealing layer (2) that is positioned at damping ring outside, described tip (7) forms insert seal with described sealing layer (2), and described sealing layer (2) is fixed on casing lining section (1) inner side.
4. according to the turbine blade damping device described in claim 2 or 3, it is characterized in that, between fin pin end face (12) and fin cover end face (13), be provided with the spring (11) for damping, spring (11) is fixed on one of them end face.
5. according to the turbine blade damping device described in claim 2 or 3, it is characterized in that, fin pin outer surface (14) is provided with the spring (11) for damping.
6. according to the turbine blade damping device described in claim 2 or 3, it is characterized in that, in the outside of fin pin or the inner side of fin cover be provided with the wearing layer for damping.
7. turbine blade damping device according to claim 1, is characterized in that, end face welding or the cast inblock of the bottom surface of described fin (3) and described blade (4).
8. turbine blade damping device according to claim 1, is characterized in that, lining section (1) direction from blade (4) to casing, and the cross section of described fin (3) reduces gradually.
9. turbine blade damping device according to claim 1, it is characterized in that, the bottom surface (6) of a plurality of fins (3) and the end face of individual blade (4) weld respectively or cast inblock, and a plurality of fins (3) end-to-end forms multi-turn for the damping ring (10) of vibration damping.
10. a turbine, is characterized in that: described turbine comprises the turbine blade damping device described in claim 1-9 any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320827740.3U CN203584480U (en) | 2013-12-13 | 2013-12-13 | Turbine blade damping device and turbine thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320827740.3U CN203584480U (en) | 2013-12-13 | 2013-12-13 | Turbine blade damping device and turbine thereof |
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| Publication Number | Publication Date |
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| CN203584480U true CN203584480U (en) | 2014-05-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201320827740.3U Expired - Lifetime CN203584480U (en) | 2013-12-13 | 2013-12-13 | Turbine blade damping device and turbine thereof |
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| CN (1) | CN203584480U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104440153A (en) * | 2014-11-04 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Damping device for machining blades in case |
| JP2017180380A (en) * | 2016-03-31 | 2017-10-05 | 三菱日立パワーシステムズ株式会社 | Stationary blade ring installed at axial flow rotary machine and axial flow rotary machine |
| US12025053B1 (en) | 2023-07-06 | 2024-07-02 | Pratt & Whitney Canada Corp. | Cantilever stator vane with damper |
-
2013
- 2013-12-13 CN CN201320827740.3U patent/CN203584480U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104440153A (en) * | 2014-11-04 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Damping device for machining blades in case |
| JP2017180380A (en) * | 2016-03-31 | 2017-10-05 | 三菱日立パワーシステムズ株式会社 | Stationary blade ring installed at axial flow rotary machine and axial flow rotary machine |
| US12025053B1 (en) | 2023-07-06 | 2024-07-02 | Pratt & Whitney Canada Corp. | Cantilever stator vane with damper |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201108 Shanghai city Minhang District Lotus Road No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140507 |