CN103061830B - A kind of turbine oscillation damping method and vibration damping structure - Google Patents
A kind of turbine oscillation damping method and vibration damping structure Download PDFInfo
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- CN103061830B CN103061830B CN201310018713.6A CN201310018713A CN103061830B CN 103061830 B CN103061830 B CN 103061830B CN 201310018713 A CN201310018713 A CN 201310018713A CN 103061830 B CN103061830 B CN 103061830B
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- turbine
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- 238000013016 damping Methods 0.000 title claims abstract description 35
- 238000000034 method Methods 0.000 title claims abstract description 25
- 230000010355 oscillation Effects 0.000 title claims abstract description 16
- 239000011248 coating agent Substances 0.000 claims abstract description 22
- 238000000576 coating method Methods 0.000 claims abstract description 22
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 20
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 20
- 239000010439 graphite Substances 0.000 claims abstract description 20
- 230000001629 suppression Effects 0.000 abstract description 11
- 230000008569 process Effects 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000009434 installation Methods 0.000 abstract description 2
- 239000002184 metal Substances 0.000 description 3
- 230000010070 molecular adhesion Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of turbine oscillation damping method and vibration damping structure, described oscillation damping method and vibration damping structure are included in turbine diaphragm and turbine end surface of contact processes reticulation patterns, and smears graphite coating in reticulation patterns; Also process reticulation patterns at turbine end face and refluence dish surface of contact, and smear graphite coating in reticulation patterns; During installation, diversion disk is pretension vertically, for keeping desirable effectiveness in vibration suppression, should adjust within the specific limits in pretension.The present invention improves on existing structure, and technique is simple, keeps original assembly technology constant, successful.
Description
Technical field
The invention belongs to aeroengine & gas turbine general structure design field, relate to a kind of rotor-support-foundation system oscillation damping method and vibration damping structure, specifically, refer to a kind of turbine oscillation damping method and vibration damping structure.
Background technique
In microminiature gas turbine general structure design, meeting arrange diversion disk in turbine front end and its pretension is installed, and object is to compress turbine blade tenon, prevents from loosening (for split type turbine); Meanwhile, in air system, play sealing, guide functions (for split type & integrated type turbine).Traditional turbine damping technology many employings elastic damper, magnetic bearing, foil bearing and dry friction damping technology etc., although these damping technologies can reduce the vibration of rotor-support-foundation system especially turbine to a certain extent, but there is mounting structure complexity, the more high deficiency of cost, and be unfavorable for controlling the vibration of all directions such as turbine end transverse vibration, shimmy, torsional oscillation.Thus, be necessary to improve existing turbine damping technology, to simplify form and the mounting process of turbine vibration damping structure, improve effectiveness in vibration suppression simultaneously, effectively control the vibration of all directions such as turbine end transverse vibration, shimmy, torsional oscillation.
Summary of the invention
The object of the invention is to utilize existing design of part, at existing structure, functionally, under the prerequisite of complexity not increasing system architecture, a kind of novel turbine oscillation damping method and vibration damping structure are proposed, to coordinate rotor-support-foundation system vibration damping scheme, more effectively control the vibration of all directions such as turbine end transverse vibration, shimmy, torsional oscillation.
According to an aspect of the present invention, provide a kind of turbine oscillation damping method, it is characterized in that, described method comprises:
Turbine diaphragm is fixedly set in the wheel hub of turbine;
Turbine diaphragm vertically pretension is fitted on turbine, makes the tight contact of end outer edge surface of turbine diaphragm with the rubbing contact between both increases on turbine end face,
The described end outer edge surface and described turbine end face of turbine diaphragm are processed with reticulation patterns respectively, and graphite coating is applied in described reticulation patterns, utilize the phase mutual friction of the graphite coating on described end outer edge surface and described turbine end face to consume vibrational energy, reach the object to turbine vibration damping.
Preferably, turbine diaphragm vertically pretension is fitted on turbine, makes the raw distortion to a certain degree of turbine diaphragm, compresses turbine disk end face.
Preferably, smear certain thickness graphite coating at surface profile, the complete grid coverage decorative pattern of this graphite coating, prevents metal grill rubbing against one another.
Preferably, the frictional fit face of described end outer edge surface and described turbine end face is strengthened, to strengthen effectiveness in vibration suppression.Preferably, set up the larger friction ring of outer surface in the end of turbine diaphragm, described end outer edge surface is formed on the outer surface of friction ring.
Preferably, for ensureing best effectiveness in vibration suppression, diversion disk axial pretightening amount should adjust within the specific limits, makes the vibrational energy of turbine end can overcome the stiction in frictional fit face.
Preferably, turbine connects by assembling pin interference fit with turbine diaphragm, and pin along the circumferential direction distributes.
According to an aspect of the present invention, additionally provide a kind of turbine vibration damping structure, comprise turbine diaphragm and turbine, described turbine diaphragm is fixedly set in the wheel hub of turbine, it is characterized in that, turbine diaphragm vertically pretension is fitted on turbine, and the end outer edge surface of turbine diaphragm is pressed on turbine end face
The end outer edge surface and turbine end face of turbine diaphragm are processed with reticulation patterns respectively, at described reticulation patterns surface coating graphite coating.
Preferably, described turbine connects by assembling pin interference fit with turbine diaphragm, and pin along the circumferential direction distributes.
Preferably, arrange friction ring in the end of turbine diaphragm, described end outer edge surface is formed on the outer surface of friction ring.Namely the contact friction face of turbine diaphragm and turbine end can process separately a part, and by this weld parts at the former rubbing surface of diversion disk, then coordinates with turbine and install.
Preferably, reticulation patterns tilt angle can be 45 ° or other is arbitrarily angled; Trellis-type can be square grid or other arbitrary polygon.
In the present invention, turbine diaphragm is thin walled structures, carries out axial pretightening during installation to it, produces distortion to a certain degree, compresses turbine disk end face.The fitting surface of the two processes latticed decorative pattern, and smears certain thickness graphite coating at surface profile, this coating should be able to grid coverage decorative pattern, prevents metal grill rubbing against one another.Now, the area of fitting surface is larger, and effectiveness in vibration suppression is by better.Axial pre tightening force should change in an OK range, the effectiveness in vibration suppression of guarantee the best.When pretightening force is too small, frictional fit face positive pressure is little, and the vibrational energy that frictional force consumes is relatively little, and effectiveness in vibration suppression reduces relatively; When pretightening force is excessive, the vibrational energy of turbine end cannot overcome the stiction in frictional fit face, produces Relative friction, also just cannot consume vibrational energy, reach the object of vibration damping, and now diversion disk becomes as a whole common vibration with turbine.Within the scope of suitable pretightening force, tangential molecular adhesion power between graphitic molecules, can be produced.In micro-scale, with the drive of turbine, overcome molecular adhesion power, the displacement in random direction occurs, thus consume a large amount of vibrational energies.And the ability of absorbing vibrational energy, improve with vibration frequency and significantly improve.The resistant to elevated temperatures characteristic of graphite, make its can under the environment of turbine end high temperature long-time reliably working.
Advantage of the present invention: form is simple, technique is simple, and effectiveness in vibration suppression is obvious.
Accompanying drawing explanation
The assembling schematic diagram that Fig. 1 (a) is turbine diaphragm and turbine; Fig. 1 (b) is for A-A in Fig. 1 (a) is to generalized section; Fig. 1 (c) is the partial enlarged drawing of I in Fig. 1 (a);
Fig. 2 is the partial cutaway schematic of turbine diaphragm;
Fig. 3 fitting surface reticulation patterns schematic shapes;
Fig. 4 is the structural representation that the end of turbine diaphragm adds friction ring.
Embodiment
For making object of the present invention, technological scheme and advantage clearly understand, to develop simultaneously embodiment referring to accompanying drawing, the present invention is described in more detail.
As shown in Figures 1 to 3, the invention provides a kind of turbine oscillation damping method and vibration damping structure, turbine diaphragm 2 is fixedly set in the wheel hub of turbine 1, preferably, see Fig. 1 (b), turbine 1 connects by assembling pin interference fit with turbine diaphragm 2, and pin along the circumferential direction distributes.Turbine diaphragm 2 vertically pretension is fitted in (see Fig. 1 (a), Fig. 1 (c)) on the end face of turbine 1, turbine diaphragm 2 is thin walled structures, when its axial pretightening is installed, make its outer end produce distortion to a certain degree vertically, be pressed on turbine end face.End 202 compression fit of such turbine diaphragm 2 on turbine end face 101 with the rubbing contact between both increasing.The end outer edge surface 201 and turbine end face 101 of the end 202 of turbine diaphragm 2 are all processed with reticulation patterns 203(see Fig. 3), and at the certain thickness graphite coating of described reticulation patterns 203 surface coating, utilize the mutual frictional force of the graphite coating be separately positioned on end outer edge surface 201 and turbine end face 101 to consume the vibrational energy of turbine, reach the object to turbine vibration damping.When described reticulation patterns 203 surface coating graphite coating, the complete grid coverage decorative pattern of graphite coating should be ensured, prevent metal grill rubbing against one another.Preferably, reticulation patterns tilt angle can be 45 ° or other is arbitrarily angled; Trellis-type can be square grid or other arbitrary polygon.Can insight in advance, strengthen the frictional fit face of described end outer edge surface 201 and described turbine end face 101, can effectiveness in vibration suppression be strengthened.
When turbine diaphragm 2 is installed, axial pre tightening force should be made to control to change in an OK range, the effectiveness in vibration suppression of guarantee the best.When pretightening force is too small, frictional fit face positive pressure is little, and the vibrational energy that frictional force consumes is relatively little, and effectiveness in vibration suppression reduces relatively; When pretightening force is excessive, the vibrational energy of turbine end cannot overcome the stiction in frictional fit face, produces Relative friction, also just cannot consume vibrational energy, reach the object of vibration damping, and now diversion disk becomes as a whole common vibration with turbine.Within the scope of suitable pretightening force, between graphitic molecules, molecular adhesion power can be produced, in micro-scale, with the drive of turbine, the displacement in random direction occur, thus consume a large amount of vibrational energies.The resistant to elevated temperatures characteristic of graphite, make its can under the environment of turbine end high temperature long-time reliably working.
In some embodiments of the invention, as shown in Figure 4, the end outer edge surface 201 of turbine diaphragm 2 is not directly formed on the end 201 of turbine diaphragm 2, but the larger friction ring of an outer surface 5 is welded on the end 202 of turbine diaphragm 2, end outer edge surface 201 is formed on the outer surface 501 of friction ring 5, process decorative pattern on a surface, smear graphite.Namely turbine diaphragm 2 can process separately a part with the contact friction face of turbine end, and by this weld parts at the former rubbing surface of diversion disk, then coordinates with turbine and install.This is applicable to the situation needing to increase friction area and the limited inconvenience setting of turbine diaphragm wall thickness, can carry out transition connection by friction ring.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within the scope of the present invention.
Claims (5)
1. a turbine oscillation damping method, is characterized in that, described method comprises:
Turbine diaphragm is fixedly set in the wheel hub of turbine;
Turbine diaphragm vertically pretension is fitted on turbine, make turbine diaphragm generation distortion to a certain degree, make the tight contact of end outer edge surface of turbine diaphragm on turbine end face with the rubbing contact between both increases, turbine diaphragm axial pretightening amount adjusts within the specific limits, the vibrational energy of turbine end is made to overcome the stiction in frictional fit face
The described end outer edge surface and described turbine end face of turbine diaphragm are processed with reticulation patterns respectively, and at described reticulation patterns surface coating graphite coating, utilize the phase mutual friction of the graphite coating on described end outer edge surface and described turbine end face to consume vibrational energy, reach the object to turbine vibration damping; Described graphite coating covers reticulation patterns completely, prevents reticulation patterns rubbing against one another;
Arrange friction ring in the end of turbine diaphragm, described end outer edge surface is formed on the outer surface of friction ring, and the area of described friction ring outer surface is greater than the surface area of turbine diaphragm end when not arranging friction ring.
2. turbine oscillation damping method according to claim 1, is characterized in that, turbine connects by assembling pin interference fit with turbine diaphragm, and pin along the circumferential direction distributes.
3. turbine oscillation damping method according to claim 1, is characterized in that, reticulation patterns tilt angle is 45 ° or other is arbitrarily angled; Trellis-type is square grid or other arbitrary polygon.
4. one kind in order to implement the turbine vibration damping structure of the turbine oscillation damping method described in above-mentioned any one claim, comprise turbine diaphragm and turbine, described turbine diaphragm is fixedly set in the wheel hub of turbine, it is characterized in that, described turbine diaphragm vertically pretension is fitted on turbine, make turbine diaphragm generation distortion to a certain degree, the end outer edge surface of turbine diaphragm is made to be pressed on turbine end face, turbine diaphragm axial pretightening amount adjusts within the specific limits, make the vibrational energy of turbine end can overcome the stiction in frictional fit face
The end outer edge surface and turbine end face of turbine diaphragm are processed with reticulation patterns respectively, in described reticulation patterns, apply graphite coating; Described graphite coating covers reticulation patterns completely, prevents reticulation patterns rubbing against one another;
Arrange friction ring in the end of turbine diaphragm, described end outer edge surface is formed on the outer surface of friction ring.
5. turbine vibration damping structure according to claim 4, is characterized in that, described turbine connects by assembling pin interference fit with turbine diaphragm, and pin along the circumferential direction distributes.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310018713.6A CN103061830B (en) | 2013-01-17 | 2013-01-17 | A kind of turbine oscillation damping method and vibration damping structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310018713.6A CN103061830B (en) | 2013-01-17 | 2013-01-17 | A kind of turbine oscillation damping method and vibration damping structure |
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| CN103061830A CN103061830A (en) | 2013-04-24 |
| CN103061830B true CN103061830B (en) | 2015-09-30 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104594954B (en) * | 2014-12-15 | 2016-01-06 | 中国南方航空工业(集团)有限公司 | Turbine structure and there is its gas turbine |
| CN104895622B (en) * | 2015-06-24 | 2016-08-24 | 中国航空动力机械研究所 | A kind of gas turbine flow guiding disc |
| FR3047075B1 (en) * | 2016-01-27 | 2018-02-23 | Safran Aircraft Engines | REVOLUTION PIECE FOR TURBINE TEST BENCH OR FOR TURBOMACHINE, TURBINE TESTING BENCH COMPRISING THE TURBINE, AND PROCESS USING THE SAME |
| CN113606000B (en) * | 2021-07-28 | 2023-03-14 | 中国科学院工程热物理研究所 | Disc rotor system with vibration damping and weight reducing functions |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2844554Y (en) * | 2005-11-08 | 2006-12-06 | 慈兴集团有限公司 | Sealing ring of bearing |
| CN101333940A (en) * | 2007-06-26 | 2008-12-31 | 斯奈克玛 | Rotor wheel for a jet engine, and jet engine comprising same |
| CN202370590U (en) * | 2011-11-25 | 2012-08-08 | 中国航空动力机械研究所 | Turbine blade structure |
| CN202578804U (en) * | 2012-04-13 | 2012-12-05 | 中国航空动力机械研究所 | Densification device for turbine rabbet |
| CN203097959U (en) * | 2013-01-17 | 2013-07-31 | 中国科学院工程热物理研究所 | Turbine vibration reduction structure |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0505978D0 (en) * | 2005-03-24 | 2005-04-27 | Alstom Technology Ltd | Interlocking turbine blades |
| US7654794B2 (en) * | 2005-11-17 | 2010-02-02 | General Electric Company | Methods and apparatus for assembling steam turbines |
| US9500242B2 (en) * | 2008-12-05 | 2016-11-22 | GM Global Technology Operations LLC | Component with inlay for damping vibrations |
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2013
- 2013-01-17 CN CN201310018713.6A patent/CN103061830B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2844554Y (en) * | 2005-11-08 | 2006-12-06 | 慈兴集团有限公司 | Sealing ring of bearing |
| CN101333940A (en) * | 2007-06-26 | 2008-12-31 | 斯奈克玛 | Rotor wheel for a jet engine, and jet engine comprising same |
| CN202370590U (en) * | 2011-11-25 | 2012-08-08 | 中国航空动力机械研究所 | Turbine blade structure |
| CN202578804U (en) * | 2012-04-13 | 2012-12-05 | 中国航空动力机械研究所 | Densification device for turbine rabbet |
| CN203097959U (en) * | 2013-01-17 | 2013-07-31 | 中国科学院工程热物理研究所 | Turbine vibration reduction structure |
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| CN103061830A (en) | 2013-04-24 |
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Inventor after: Gao Jinhai Inventor after: Hu Jialin Inventor after: Guo Baoting Inventor before: Chen Wei |
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