CN104471192A - Damper system and corresponding turbine - Google Patents
Damper system and corresponding turbine Download PDFInfo
- Publication number
- CN104471192A CN104471192A CN201380038635.4A CN201380038635A CN104471192A CN 104471192 A CN104471192 A CN 104471192A CN 201380038635 A CN201380038635 A CN 201380038635A CN 104471192 A CN104471192 A CN 104471192A
- Authority
- CN
- China
- Prior art keywords
- block device
- guard shield
- turbine
- tip guard
- shield sections
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000011153 ceramic matrix composite Substances 0.000 claims description 35
- 239000002184 metal Substances 0.000 claims description 11
- 229910052751 metal Inorganic materials 0.000 claims description 11
- 238000013016 damping Methods 0.000 abstract 1
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 6
- 229910045601 alloy Inorganic materials 0.000 description 5
- 239000000956 alloy Substances 0.000 description 5
- 230000008901 benefit Effects 0.000 description 5
- 229910017052 cobalt Inorganic materials 0.000 description 3
- 239000010941 cobalt Substances 0.000 description 3
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 3
- 229910001092 metal group alloy Inorganic materials 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- 229910000601 superalloy Inorganic materials 0.000 description 3
- 239000003570 air Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229910000967 As alloy Inorganic materials 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
- F05D2300/6033—Ceramic matrix composites [CMC]
Abstract
A damper system and a turbine are provided. The damper system includes a plurality of CMC blades. Each CMC blade has a first member of a tip shroud, the first member opposite a second member of the tip shroud, a radial flange extending between the first member and the second member of the tip shroud, and at least one aperture in the radial flange for receiving a damping member, the dampening member joining and dampening adjacent CMC blades. The turbine includes a plurality of turbine blade tip shroud segments, each tip shroud segment having a first surface that cooperates with the first surface in an adjacent tip shroud segment to form a first opening, each tip shroud segment having a first receiving surface. The turbine includes a damper member that abuts the first receiving surface of each tip shroud segment.
Description
With the cross reference of related application
The name of patent application claims submission on July 20th, 2012 is called the U.S. Provisional Patent Application No.61/674 of " block device (damper) system and turbine ", the benefit of 086, the disclosure of this application is incorporated by reference herein, and just looks like that it intactly writes out herein.
Technical field
The present invention relates generally to turbine.More specifically, block device system and turbine is related to.
Background technique
Turbine assembly produces power typically via the hot compressed air volumetric expansion making combustion fuel produce to make running shaft.Gas turbine wheel blade or blade have airfoil shape substantially, and it is designed to be become by the heat energy of flow path gas the machinery of rotor to rotate with kinetic transformation.
Turbine performance and efficiency strengthen by lower person: provide Sealing at the tip place of blade, and with on the top being blocked in blade or ambient air stream, this air stream will walk around blade originally.Such as, tip guard shield can be positioned on the end of blade, and this end is relative with the end be attached on running shaft.
CMC blade brings special design challenge.CMC has intrinsic low fracture strain, and therefore lacks high centrifugal force and the bearing capacity of assembling required for pre-distortion.Therefore, CMC material system is difficult to withstand the high contact stress and warping stress that the tip guard shield that interlocked by the interference fit of assembling caused.
In addition, there is endurance issues between the tip guard shield near CMC and CMC.Lacking resistance to damaging, high rate of depreciation and being subject to impact damage makes contacting of CMC tip guard shield very undesirable.
Therefore, the block device system and the turbine that do not suffer above-mentioned defect are desirable in related domain.
Summary of the invention
According to exemplary embodiment of the present disclosure, provide a kind of block device system.Block device system comprises multiple CMC blade.Each CMC blade has: the first component of tip guard shield, and first component is relative with the second component of tip guard shield; The radial flange extended between the first component and second component of tip guard shield; And at least one aperture for receiving block device parts in radial flange, block device parts link and the adjacent CMC blade of block (dampen).
According to another exemplary embodiment of the present disclosure, provide a kind of turbine.Turbine comprises multiple turbine blade tips guard shield sections.Each tip guard shield sections has first surface, and this first surface cooperates with the first surface in adjacent tip guard shield sections and forms the first opening.Each tip guard shield sections has the first receiving surface.Turbine comprises block device parts, and it againsts the first receiving surface of each tip guard shield sections.Block device parts link and the adjacent CMC blade of block.
According to the following more detailed description of the preferred embodiment obtained by reference to the accompanying drawings, other features and advantages of the present invention will be apparent, and accompanying drawing describes principle of the present invention in an illustrative manner.
Accompanying drawing explanation
Fig. 1 is the perspective schematic view of block device system of the present disclosure.
Fig. 2 is the schematic side elevation of tip of the present disclosure guard shield sections.
Fig. 3 is the schematic side elevation comprising the tip guard shield sections of metal collet (collet) of the present disclosure.
Fig. 4 is the fragmentary, perspective view of tip of the present disclosure guard shield sections.
Fig. 5 is the schematic sectional view obtained along the line 5-5 of Fig. 4 of block device of the present disclosure.
Fig. 6 is the alternative of block device of the present disclosure.
Fig. 7 is the alternative of block device of the present disclosure.
Fig. 8 is the alternative of block device of the present disclosure.
Fig. 9 is the plan view of the turbine comprising block device of the present disclosure.
Figure 10 is the side view of the block device of Fig. 9 of the present disclosure.
When feasible, in all figure, use same reference numerals is represented same parts.
Embodiment
Provide block device system and turbine.
An advantage of embodiment of the present disclosure comprises higher turbine-entry temperature ability.Another advantage is the turbine efficiency improved.And another advantage is for reducing engine weight.
According to an embodiment, provide the block device system comprising multiple ceramic matrix composite (CMC) blade.Fig. 1 is the perspective schematic view of block device system 100 of the present disclosure.Block device system 100 can comprise multiple blade, and blade comprises CMC.CMC blade 110 can comprise platform and Dovetail, and Dovetail is for being attached to turbine (not shown).CMC blade 110 can comprise on the pressure side 112 and suction side 114.Each CMC blade 110 can comprise the first component 170 of tip guard shield 140, and first component is relative with the second component 180 of tip guard shield 140.Each CMC blade 110 can comprise radial flange 150, extends between its first component 170 at tip guard shield 140 and second component 180.Each CMC blade 110 can be included at least one aperture 200,210 in radial flange 150, and it is for receiving block device parts 160 (see Fig. 2).Block device parts 160 can link and the adjacent CMC blade 110 of block.As shown in Fig. 1, block device parts 160 can be wire, and it extends through the adjacent aperture 200,210 in each CMC blade 110.Block device parts 160 can be selected from metal, and such as, but not limited to metal, metal alloy and its combination, such as alloy can include but not limited to nickel based super alloy or cobalt base alloy.Block device parts 160 can link any amount of CMC blade 110.In the embodiment do not shown in the drawings, block device parts 160 circumferentially link CMC blade 110 on 360 degree.
According to an embodiment, CMC blade can have the structure for receiving block device parts.Such as, Fig. 2 illustrates the first aperture 200 and the second aperture 210 on radial flange 150, and it is for receiving block device parts 160.Radial flange 150 can between the first component 170 of the tip guard shield 140 of CMC blade 110 and second component 180.
According to an embodiment, CMC blade can have structure for receiving block device parts and extra hardware.Such as, Fig. 3 illustrates the metal collet 300 in the first aperture 200, and it is for fixing block device parts 160.Metal collet 300 can be made up of any suitable metallic material, and such as, but not limited to metal, metal alloy and its combination, such as, alloy can comprise nickel based super alloy or cobalt base alloy.
According to an embodiment, turbine can comprise the CMC blade with tip guard shield sections.Such as, Fig. 4 is the fragmentary, perspective view of the tip guard shield sections of turbine 102.Turbine 102 can comprise multiple turbine blade tips guard shield sections 140.
According to an embodiment, the tip guard shield sections of the adjacent CMC blade in block device system can comprise multiple surface, and it can cooperate and form opening, for reception and encirclement block device parts.Such as, as shown in Fig. 5-8, each tip guard shield sections 140 of First CMC blade 412 and second CMC blade 414 can comprise first surface 506, and it can cooperate with the first surface 506 in adjacent tip guard shield sections 140 and form the first opening 502.Each tip guard shield sections 140 can comprise the first receiving surface 510.Block device parts 160 can against the first receiving surface 510 of each tip guard shield sections 140.In one embodiment, the first surface 506 of adjacent tip guard shield sections 140 can be complementary.Such as, as shown in Fig. 5, turbine blade tip guard shield sections 140 can comprise second surface 508, and it cooperates with second surface 508 and adjacent tip guard shield sections 140 and form the second opening 504.First and second receiving surfaces 510 and 512 of adjacent tip guard shield sections 140 can surround block device parts 160.In one embodiment, as depicted in Figure 5, the second receiving surface 512 can against block device parts 160.As shown in Figure 5, block device parts 160 can be circular metal plug-in unit; But the block device parts 160 of any geometrical construction can be feasible.Suitable material for block device parts 160 includes but not limited to metal, metal alloy and its combination, and such as, alloy can comprise nickel based super alloy, cobalt base alloy.
According to an embodiment, the tip guard shield sections of the adjacent CMC blade in block device system can comprise multiple surface, and it can cooperate and be formed for receiving but not keeping the opening of block device parts.Such as, as shown in Fig. 6, block device parts 160 comprise holding member 900, and it is attached at least one end of block device parts 160.Holding member 900 can cooperate with the surface 500 of adjacent tip guard shield sections 140 and is held in place by block device parts 160.As shown in Fig. 7, block device parts 160 can have triangle geometry structure.In one embodiment, First CMC blade 412 has first surface 506, and it can cooperate with the first surface 506 of second CMC blade 414.The second surface 508 of First CMC blade can cooperate with the first surface 506 of second CMC blade 414.In the embodiment shown in the figure 7, the first receiving surface 510 and the second receiving surface 512 can surround block device parts 160, thus block device parts 160 are held in place between adjacent tip guard shield sections 140.On the contrary, as shown in Fig. 8, embodiment does not comprise the second receiving surface 512.In fact, in fig. 8, block device parts 160 can comprise holding member 900, and it can cooperate with the surface of adjacent tip guard shield sections and be held in place by block device parts 160.In one embodiment, block device parts 160 can circumferentially be fixed on tip guard shield sections 140 by holding member 900.
According to an embodiment, block device parts can comprise holding member.Such as, as shown in Fig. 9 and 10, the holding member 900 of block device parts 160 can near the first component 170 of tip guard shield sections 140 and second component 180.In an alternative embodiment, holding member 900 can not stride across the whole length of block device parts 160.
Although have references to preferred embodiment to describe the present invention, it will be understood by those skilled in the art that and can make various amendment when not departing from scope of the present invention, and equivalent can replace element of the present invention.In addition, many improvement can be made when not departing from essential scope of the present invention, being suitable for instruction of the present invention to make concrete condition or content.Therefore, it is intended that the invention is not restricted to the specific embodiment be disclosed as to perform the optimal mode that the present invention conceives, but the present invention will comprise falling all embodiments within the scope of the appended claims.
Claims (13)
1. a block device system, comprising:
Multiple CMC blade, each blade has
The first component of tip guard shield, described first component is relative with the second component of described tip guard shield;
Radial flange, extends between its first component at described tip guard shield and second component; And
At least one aperture for receiving block parts in described radial flange, described block parts link and the adjacent CMC blade of block.
2. block device system according to claim 1, it is characterized in that, block parts circumferentially link CMC blade on 360 degree.
3. block device system according to claim 1, is characterized in that, described block parts are metal.
4. block device system according to claim 1, is characterized in that, described block parts are wire.
5. block device system according to claim 1, is characterized in that, described block device system is included in the metal collet near described aperture further.
6. a turbine, comprising:
Multiple turbine blade tips guard shield sections, each tip guard shield sections has first surface, and this first surface cooperates with the first surface in adjacent tip guard shield sections and forms the first opening, and each tip guard shield sections has the first receiving surface; And
Block device parts, it againsts the first receiving surface of each tip guard shield sections.
7. turbine according to claim 6, is characterized in that, described turbine blade tip guard shield sections comprises second surface, and this second surface cooperates with the second surface in adjacent tip guard shield sections and forms the second opening.
8. turbine according to claim 6, is characterized in that, described turbine blade tip guard shield sections comprises the second receiving surface, and it againsts described block device parts.
9. turbine according to claim 6, is characterized in that, described block device comprises at least one holding member, and it is attached at least one end of described block device parts.
10. turbine according to claim 9, is characterized in that, described holding member and described block device parts form.
11. turbines according to claim 9, is characterized in that, described block device parts are circumferentially fixed on the guard shield sections of described tip by described holding member.
12. turbines according to claim 6, is characterized in that, described block device parts are metal.
13. turbines according to claim 6, is characterized in that, described multiple turbine blade tips guard shield sections is ceramic matrix composite.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201261674086P | 2012-07-20 | 2012-07-20 | |
| US61/674,086 | 2012-07-20 | ||
| US13/656,098 | 2012-10-19 | ||
| US13/656,098 US20140023506A1 (en) | 2012-07-20 | 2012-10-19 | Damper system and a turbine |
| PCT/US2013/046963 WO2014014616A1 (en) | 2012-07-20 | 2013-06-21 | Damper system and corresponding turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104471192A true CN104471192A (en) | 2015-03-25 |
Family
ID=49946696
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380038635.4A Pending CN104471192A (en) | 2012-07-20 | 2013-06-21 | Damper system and corresponding turbine |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US20140023506A1 (en) |
| EP (1) | EP2885505A1 (en) |
| JP (1) | JP2015524891A (en) |
| CN (1) | CN104471192A (en) |
| BR (1) | BR112015001224A2 (en) |
| CA (1) | CA2879380A1 (en) |
| WO (1) | WO2014014616A1 (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10316673B2 (en) | 2016-03-24 | 2019-06-11 | General Electric Company | CMC turbine blade platform damper |
| US10724380B2 (en) | 2017-08-07 | 2020-07-28 | General Electric Company | CMC blade with internal support |
| CN109026172B (en) * | 2018-09-25 | 2024-02-02 | 中国船舶重工集团公司第七0三研究所 | From banded damping lacing wire strip vibration attenuation structure of taking guan leaf |
| FR3113300B1 (en) * | 2020-08-06 | 2023-12-22 | Safran Aircraft Engines | Turbomachine rotor blade |
| US11536144B2 (en) | 2020-09-30 | 2022-12-27 | General Electric Company | Rotor blade damping structures |
| US11739645B2 (en) | 2020-09-30 | 2023-08-29 | General Electric Company | Vibrational dampening elements |
| FR3137128A1 (en) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Turbomachine assembly comprising blades carrying lips and a cable connecting the lips to each other |
| FR3137124A1 (en) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Turbomachine assembly comprising blades carrying liplets whose ends overlap each other in the circumferential direction |
| FR3137127A1 (en) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Bladed turbomachine assembly comprising means of limiting vibrations between platforms |
| FR3137122A1 (en) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Bladed assembly with inter-platform connection by friction member |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2942843A (en) * | 1956-06-15 | 1960-06-28 | Westinghouse Electric Corp | Blade vibration damping structure |
| US3377050A (en) * | 1966-06-21 | 1968-04-09 | Bristol Siddeley Engines Ltd | Shrouded rotor blades |
| CN87101148A (en) * | 1986-12-22 | 1988-07-13 | 西屋电气公司 | The integral (tip) shroud turbine blade of " V " otch and measure admittedly method with the wearing and tearing of tight ness rating and moving blade |
| US6409472B1 (en) * | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
| WO2011086313A1 (en) * | 2010-01-13 | 2011-07-21 | Snecma | Vibration damper having a pin between adjacent turbine engine rotor-wheel blade roots made of a composite material |
| FR2960021A1 (en) * | 2010-05-12 | 2011-11-18 | Snecma | Rotor wheel for use in low-pressure turbine stage of jet engine, has annular vibration damping rod mounted around shrouds of ceramic matrix composite vanes and maintained on shrouds of vanes by upstream and downstream hooks |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1723321A (en) * | 1929-08-06 | of baden | ||
| US6482533B2 (en) * | 2001-03-05 | 2002-11-19 | The Boeing Company | Article having imbedded cavity |
| US8714932B2 (en) * | 2008-12-31 | 2014-05-06 | General Electric Company | Ceramic matrix composite blade having integral platform structures and methods of fabrication |
| FR2955608B1 (en) * | 2010-01-26 | 2013-01-11 | Snecma | LAMINATED VIBRATION SHOCK ABSORBER AND SHOES BETWEEN ADJACENT BLADE HEADS IN COMPOSITE MATERIAL OF A TURBOMACHINE MOBILE WHEEL. |
| FR2956152B1 (en) * | 2010-02-09 | 2012-07-06 | Snecma | VIBRATION DAMPING DEVICE BETWEEN ADJACENT BLADE HEADS IN COMPOSITE MATERIAL OF A MOBILE TURBOMACHINE WHEEL. |
| FR2957969B1 (en) * | 2010-03-26 | 2013-03-29 | Snecma | DEVICE FOR SEALING BETWEEN ADJACENT BLADE HEADS IN MATERIAL COMPOSED OF A TURBOMACHINE MOBILE WHEEL |
| FR2975123B1 (en) * | 2011-05-13 | 2013-06-14 | Snecma Propulsion Solide | ROTOR OF TURBOMACHINE COMPRISING AUBES IN COMPOSITE MATERIAL WITH REPORTED HEEL |
-
2012
- 2012-10-19 US US13/656,098 patent/US20140023506A1/en not_active Abandoned
-
2013
- 2013-06-21 WO PCT/US2013/046963 patent/WO2014014616A1/en active Application Filing
- 2013-06-21 BR BR112015001224A patent/BR112015001224A2/en not_active IP Right Cessation
- 2013-06-21 CN CN201380038635.4A patent/CN104471192A/en active Pending
- 2013-06-21 EP EP13734256.4A patent/EP2885505A1/en not_active Withdrawn
- 2013-06-21 JP JP2015523095A patent/JP2015524891A/en active Pending
- 2013-06-21 CA CA2879380A patent/CA2879380A1/en not_active Abandoned
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2942843A (en) * | 1956-06-15 | 1960-06-28 | Westinghouse Electric Corp | Blade vibration damping structure |
| US3377050A (en) * | 1966-06-21 | 1968-04-09 | Bristol Siddeley Engines Ltd | Shrouded rotor blades |
| CN87101148A (en) * | 1986-12-22 | 1988-07-13 | 西屋电气公司 | The integral (tip) shroud turbine blade of " V " otch and measure admittedly method with the wearing and tearing of tight ness rating and moving blade |
| US6409472B1 (en) * | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
| WO2011086313A1 (en) * | 2010-01-13 | 2011-07-21 | Snecma | Vibration damper having a pin between adjacent turbine engine rotor-wheel blade roots made of a composite material |
| FR2960021A1 (en) * | 2010-05-12 | 2011-11-18 | Snecma | Rotor wheel for use in low-pressure turbine stage of jet engine, has annular vibration damping rod mounted around shrouds of ceramic matrix composite vanes and maintained on shrouds of vanes by upstream and downstream hooks |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2879380A1 (en) | 2014-01-23 |
| BR112015001224A2 (en) | 2017-07-04 |
| WO2014014616A1 (en) | 2014-01-23 |
| EP2885505A1 (en) | 2015-06-24 |
| US20140023506A1 (en) | 2014-01-23 |
| JP2015524891A (en) | 2015-08-27 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150325 |