GB2467582A - Vibration damper assembly - Google Patents
Vibration damper assembly Download PDFInfo
- Publication number
- GB2467582A GB2467582A GB0902032A GB0902032A GB2467582A GB 2467582 A GB2467582 A GB 2467582A GB 0902032 A GB0902032 A GB 0902032A GB 0902032 A GB0902032 A GB 0902032A GB 2467582 A GB2467582 A GB 2467582A
- Authority
- GB
- United Kingdom
- Prior art keywords
- passages
- assembly
- assembly according
- vibration damper
- damper
- 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.)
- Granted
Links
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 14
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 7
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 6
- 239000000956 alloy Substances 0.000 claims abstract description 6
- 230000000712 assembly Effects 0.000 claims description 7
- 238000000429 assembly Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 6
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims description 3
- 239000002184 metal Substances 0.000 abstract 1
- 229910052751 metal Inorganic materials 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 15
- 238000013016 damping Methods 0.000 description 13
- 230000001360 synchronised effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000002028 premature Effects 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 230000001010 compromised effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010355 oscillation 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
-
- 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
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/505—Shape memory behaviour
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A vibration damper assembly 36 is provided between two shrouds 34 of adjacent turbine blades 30. A pair of confronting passages 38 are provided, one in each of the shrouds 34 and a vibration damper 40 is located in both of the confronting passages 38. The vibration damper 40 comprises a structure which when heated expands outwardly so as to engage with the walls of the passages 38. The vibration damper 40 may be a sheet metal shape memory nickel base alloy wound into an open spiral and provided in circular cross-section passages 38.
Description
VIBRATION DAMPER ASSEMBLY
This invention relates to vibration damper assemblies, vibration damper assemblies usable between turbine shrouds of a gas turbine engine, a turbine assembly incorporating such vibration damper assemblies, and also a gas turbine engine incorporating one or more such turbine assemblies.
Gas turbine engines commonly include an axial flow turbine that comprises at least one annular array of radially extending aerofoil blades mounted on a common disc. Each aerofoil blade is sometimes provided with a shroud at its radially outer tip so that the shrouds of adjacent blades cooperate to define a radially outer circumferential boundary to the gas flow over the aerofoil blades.
In operation, there can be a tendency for the gas flows over the aerofoil blades to cause the blades to vibrate to such an extent that they require some degree of damping. One way of achieving such damping is to interconnect the shrouds of the blades with a single length of wire that passes through appropriate circuinferentially extending passages provided in the shrouds. Any vibration of the blades results in relative movement between their shrouds and hence between the passages and the wire.
Friction between the passage walls and the wire tends to dampen such relative movement, and hence the blade vibration. Such an arrangement is described and shown in Swiss Patent No. 666326. The drawback with this type of arrangement, however, is that the wire adds undesirable weight to the blade assembly.
EP0806545B1 discloses a damper for damping non-synchronous vibration in adjacent shrouded aerofoil blades in the form of pin that locates in confronting passages in adjacent blade shrouds. The pin is provided with larger diameter portions that are located totally within the passages and frictionally engage the surfaces of the passages to provide vibration damping. The pin is circular in cross section and the larger diameter pin portions are interconnected by a central, thinner portion. The configuration of the pin reduces the likelihood of it wearing in such a manner that it jams in the passages and no longer provides vibration damping. However, during engine running the damper experiences excessive wear resulting in loss of material and a reduction in damper mass. Due to the small size of the damper, this mass loss constitutes a significant proportion of its mass. The reduction in damper mass causes damping effectiveness to be compromised with time, and can result in an in service failure.
According to the present invention there is provided a vibration damper assembly, the assembly including a vibration damper located in both of a pair of generally confronting passages, the passages being provided respectively in adjacent components, the vibration damper comprising a structure which when heated expands outwardly so as to engage with the walls of the passages.
The structure may initially be compressed prior to insertion into the component passages.
The structure may be in the form of a spiral, and may be a spiral of a sheet material, which spiral may be curved about a transverse direction of an elongate sheet.
The passages may be substantially circular in cross section.
In an alternative arrangement the structure may have a pleated configuration. The pleated configuration may include sheets of material interconnected to respective adjacent sheets along opposite side edges.
The passages may be substantially rectangular in cross section.
The structure may be made of a shape memory alloy.
The structure may be made of a nickel based alloy.
The invention also provides a vibration damper assembly usable between turbine shrouds of a gas turbine engine, the assembly being according to any of the preceding eight paragraphs.
The invention moreover provides a turbine assembly for a gas turbine engine, the assembly including a vibration damper assembly according to the above paragraph between each adjacent pair of turbine blades.
The invention yet further provides a gas turbine engine incorporating one or more turbine assemblies according to the above paragraph.
Embodiments of the present invention will now be described by way of example only and with reference to the accompanying drawings, in which:-Fig. 1 is a simplified sectioned side view of a gas turbine engine incorporating the present invention; Fig. 2 is a partially exploded view of part of the turbine of the gas turbine engine shown in Fig. 1; Fig. 3 is a section through adjacent shrouds of turbine blades including a prior art vibration damper; Fig. 4 is a diagrammatic side view of a damper assembly according to the invention extending between two turbine blades; and Fig. 5 is a perspective view of a first vibration damper according to the invention; Figs. 6A and 6B are diagrammatic end views of the damper of Fig. 4 in respectively cold and heated conditions; Fig. 7 is a diagrammatic perspective view of a second vibration damper according to the invention; and Figs. 8A and 8B are respectively diagrammatic end views of the second damper of Fig. 7 in respectively cold and heated conditions.
With reference to Fig. 1, a ducted fan gas turbine engine generally indicated at 10 is of generally conventional configuration and operation. It comprises a core unit 11 which services to drive a propulsive ducted fan 12 and also to provide propulsive thrust. The core unit 11 includes a low pressure turbine 13 which comprises three rotary stages of aerofoil blades.
Part of one of those low pressure turbine stages can be seen in Fig. 2. It comprises a disc 14 having a plurality of similar radially extending aerofoil blades 15 mounted on its periphery. Each aerofoil blade 15 is preferably formed from a suitable nickel base alloy and has a conventional fir tree cross-section root 16 which locates in a correspondingly shaped slot 17 provided in the disc 14 periphery. The configuration of the root 16 ensures radial constraint of its corresponding aerofoil blade 15 whilst permitting the root 16 to be slid axially into its corresponding slot 17 in the disc periphery for assembly purposes. Suitable stops (not shown) and seal plates 18 which are subsequently attached to the disc 14 and aerofoil blades 15 ensure the axial retention of the aerofoil blades 15 on the disc.
In addition to having a root 16, each aerofoil blade comprises an inner platform 19 positioned adjacent the root 16, an aerofoil portion 20 extending radially outwardly from the inner platform 19 and a shroud 21 positioned on the radially outer extent of the aerofoil portion 20. The inner platforms 19 of adjacent aerofoil blades 15 cooperate to define a radially inner boundary to the gas path over the aerofoil portions 20. Similarly, the shrouds 21 of adjacent aerofoil blades 15 cooperate to define a radially outer boundary to the gas path over the aerofoil portions 20.
Each of the inner platforms 19 and outer shrouds 21 is circumferentially spaced apart by a small distance from its adjacent platform 19 or shroud 21. This is to allow for the vibration of the aerofoil blades 15 which inevitably occurs when gases flow over them during operation of the engine 10. It is this gas flow which causes the aerofoil blades 15 to rotate the disc 14 upon which they are mounted.
Excessive aerofoil blade vibration is usually looked upon as being undesirable since it can lead to premature component failure through cracking. The present invention is concerned with the damping of vibration in order to avoid such premature component failure.
In EP0806545 vibration damping is provided by dampers that are associated with each of the shrouds 21. Each shroud 21 is provided at each of its circumferential edges 22 with a blind circumferentially extending circular cross section passage 23. Each passage 23, as can be seen more clearly in Fig. 3, confronts the passage in the adjacent shroud 21. Each pair of confronting shroud passages 23 contains a damper 24 which is in the form of a metallic pin interconnecting the adjacent shroud passages 23. The pin 24, which is preferably formed from a nickel base alloy, is of circular cross sectional configuration and has portions that are of greater diameter than other portions. More specifically, the pin 24 has two similar larger diameter portions 25 that are interconnected by a small diameter portion 26.
Additionally the pin 24 diameter varies progressively from its smaller diameter central portion 26 to each of its larger diameter portions 25 and thence decreases to each of its ends.
The greatest circumference part of each larger diameter pin portion 25 is so positioned on the pin 24 that each of the portions 25 of the pin 24 that engages the internal wall of its associated shroud passage 23 is totally contained within that passage 23.
If the aerofoil blades 15 are subject in use to non-synchronous vibration, there will be relative movement between the blades 15. Since the aerofoil blades 15 are attached to the disc 14 at their radially inner extends, that relative movement tends to be of greatest magnitude in the region of the blade shrouds 21. The vibration is likely to be in one or both of the two main modes: flutter and torsional oscillation. Notwithstanding the particular mode or modes involved, vibration of the blades 15 results in adjacent shrouds 21 moving relative to each other in both circumferential and axial directions (with respect to the longitudinal axis of the engine 10) . Such relative shroud 21 movement results in the pins 24 sliding within the passages 23. This sliding movement is resisted by friction between the walls of the passages 23 and those portions of the pins 24 that engage those walls, thereby providing damping of the movement. The pins 24 therefore provide damping of non-synchronous vibration of adjacent aerofoil blades 15.
Fig. 4 shows two adjacent turbine blades 30 each with an aerofoil 32 and an outer shroud 34. A vibration damper assembly 36 is provided between the two shrouds 34. The assembly 36 includes a pair of confronting passages 38 one in each of the shrouds 34. A vibration damper 40 (Fig. 5) is provided located in each of the passages 38 and extending therebetween.
The damper 40 comprises an open spiral structure formed from a sheet of a shape memory nickel based alloy, with the spiral being wrapped around the transverse direction of an elongate sheet. To locate the damper 40 in the passages 38 it is compressed to have an outer circumference which is less than the inner diameter of the passages 38. The compressed damper 40 is located cold into the passages 38.
In use, the heat in the turbine will cause the damper to expand to engage the inner walls of the passages 38, and provide a damping effect. As and when the damper 40 becomes worn, the structure thereof will simply expand outwardly a little more due to the heat in the turbine, and therefore to maintain its damping effect. The expansion of the damper 40 can be seen in Figs. 6A and 6B, where Fig. 6A is the damper 40 when cold, and heat in the turbine urges the damper to unroll as shown in Fig. 6B.
Figs. 7, 8A and 8B show a second alternative damper 42. In this instance the damper 42 is made from a number of sheets 44 of a nickel base shape memory alloy Ira a pleated configuration. Alternate sheets 44 are provided generally parallel to each other, with further sheets 46 extending diagonally therebetween. The sheets 46 extend between opposite side edges of the alternate sheets 44.
The damper 42 can be used in a similar manner to the damper 40, with the damper 42 being compressed before insertion in the passages 38. For use with the first damper 40 the passages 38 will generally have a circular cross section, whilst for use with the damper 42 the passages may have a rectangular configuration. Figs. 8A and 8B show expansion of the damper 42 upon heating, with the pleated stack of sheets 44, 46 tending to expand outwardly.
There is thus described a vibration damper assembly where the damper automatically expands with heat in the respective passages, and therefore as the damper is worn the structure of the damper will expand to maintain engagement with the walls of the passages. This helps to overcome the problems encountered previously with dampers where as the dampers have worn this has overtime reduced their damping effectiveness and can eventually result in a failure in service.
The dampers of the present invention are still of relatively straightforward construction and thus can be inexpensively produced for operation in a conventional manner.
Various other modifications may be made without departing from the scope of the invention. For instance, whilst the vibration damper assembly described above is for use with turbine shrouds, assemblies according to the invention could be used in a wide range of different applications. The damper may take a different form to those described. The damper may be made of different materials.
Claims (14)
- Claims 1. A vibration damper assembly, the assembly including a vibration damper located in both of a pair of generally confronting passages, the passages being provided respectively in adjacent components, the vibration damper comprising a structure which when heated expands outwardly so as to engage with the walls of the passages.
- 2. An assembly according to claim 1, characterised in that the structure is initially compressed prior to insertion into the component passages.
- 3. An assembly according to claims 1 or 2, characterised in that the structure is in the form of a spiral.
- 4. An assembly according to claim 3, characterised in that the structure is in the form of a spiral of a sheet material.
- 5. An assembly according to claim 4 characterised Ira that the structure is in the form of a spiral curved about a transverse longitudinal direction of an elongate sheet.
- 6. An assembly according to any of the preceding claims, characterised in that the passages are substantially circular in cross section.
- 7. An assembly according to claims 1 or 2, characterised in that the structure has a pleated configuration.
- 8. An assembly according to claim 7, characterised in that the pleated configuration includes sheets of material interconnected to respective adjacent sheets along opposite side edges.
- 9. An assembly according to claims 7 or 8, characterised in that the passages are substantially rectangular in cross section.
- 10. An assembly according to any of the preceding claims, characterised in that the structure is made of a shape memory alloy.
- 11. An assembly according to any of the preceding claims, characterised in that the structure is of a nickel based alloy.
- 12. A vibration damper assembly useable between turbine shrouds of a gas turbine engine, characterised in that the assembly is according to any of the preceding claims.
- 13. A turbine assembly for a gas turbine engine, the assembly including a vibration damper assembly according to claim 12 between each adjacent pair of turbine blades.
- 14. A gas turbine engine incorporating one or more turbine assemblies according to claim 13.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0902032A GB2467582B (en) | 2009-02-10 | 2009-02-10 | Vibration damper assembly |
US12/699,157 US8596980B2 (en) | 2009-02-10 | 2010-02-03 | Vibration damper assembly |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0902032A GB2467582B (en) | 2009-02-10 | 2009-02-10 | Vibration damper assembly |
Publications (3)
Publication Number | Publication Date |
---|---|
GB0902032D0 GB0902032D0 (en) | 2009-03-11 |
GB2467582A true GB2467582A (en) | 2010-08-11 |
GB2467582B GB2467582B (en) | 2011-07-06 |
Family
ID=40469744
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB0902032A Expired - Fee Related GB2467582B (en) | 2009-02-10 | 2009-02-10 | Vibration damper assembly |
Country Status (2)
Country | Link |
---|---|
US (1) | US8596980B2 (en) |
GB (1) | GB2467582B (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2492449A1 (en) * | 2011-02-28 | 2012-08-29 | Alstom Technology Ltd | Sealing arrangement for a thermal machine |
US20130052032A1 (en) * | 2010-01-26 | 2013-02-28 | Herakles | Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel |
WO2015044699A1 (en) | 2013-09-26 | 2015-04-02 | Franco Tosi Meccanica S.P.A. | Rotor stage of axial turbine with an adaptive regulation to dynamic stresses |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2468528B (en) * | 2009-03-13 | 2011-03-30 | Rolls Royce Plc | Vibration damper |
FR2955142B1 (en) * | 2010-01-13 | 2013-08-23 | Snecma | PIONE VIBRATION SHOCK ABSORBER BETWEEN ADJACENT AUB THREADS IN COMPOSITE MATERIAL OF A TURBOMACHINE MOBILE WHEEL. |
EP2803821A1 (en) * | 2013-05-13 | 2014-11-19 | Siemens Aktiengesellschaft | Blade device, blade system, and corresponding method of manufacturing a blade system |
US9765625B2 (en) * | 2013-05-23 | 2017-09-19 | MTU Aero Engines AG | Turbomachine blade |
EP2806106A1 (en) | 2013-05-23 | 2014-11-26 | MTU Aero Engines GmbH | Blade of a turbomachine having an impulse body |
US10648347B2 (en) | 2017-01-03 | 2020-05-12 | General Electric Company | Damping inserts and methods for shrouded turbine blades |
IT201900013854A1 (en) | 2019-08-02 | 2021-02-02 | Ge Avio Srl | TURBINE MOTOR WITH SNAP-IN GASKETS. |
US11174739B2 (en) * | 2019-08-27 | 2021-11-16 | Solar Turbines Incorporated | Damped turbine blade assembly |
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 |
CN114508386B (en) * | 2020-11-16 | 2024-06-25 | 中国航发商用航空发动机有限责任公司 | Vane damper, turbine and aeroengine |
US12071895B2 (en) * | 2021-04-13 | 2024-08-27 | Ge Infrastructure Technology Llc | Turbine load coupling cooling system |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2912223A (en) * | 1955-03-17 | 1959-11-10 | Gen Electric | Turbine bucket vibration dampener and sealing assembly |
GB1503453A (en) * | 1975-10-28 | 1978-03-08 | Europ Turb Vapeur | Rotor of a turbomachine |
US4815938A (en) * | 1987-12-24 | 1989-03-28 | Westinghouse Electric Corp. | Shroud gap control for integral shrouded blades |
JPH0539701A (en) * | 1991-08-06 | 1993-02-19 | Fuji Electric Co Ltd | Cascade of turbine moving blade |
US5984638A (en) * | 1994-08-12 | 1999-11-16 | Elliott Turbomachinery Co., Inc. | Turbomachine radial impeller vibration constraining and damping mechanism |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3752599A (en) * | 1971-03-29 | 1973-08-14 | Gen Electric | Bucket vibration damping device |
GB1358798A (en) * | 1972-06-09 | 1974-07-10 | Bbc Sulzer Turbomaschinen | Sealing element for a turbo-machine |
FR2291349A1 (en) * | 1974-11-14 | 1976-06-11 | Europ Turb Vapeur | PROVISION FOR CONTINUOUS LINKAGE OF MOBILE BLADES OF A TURBO-MACHINE |
US3986792A (en) * | 1975-03-03 | 1976-10-19 | Westinghouse Electric Corporation | Vibration dampening device disposed on a shroud member for a twisted turbine blade |
JPH0791206A (en) * | 1993-09-24 | 1995-04-04 | Mitsubishi Heavy Ind Ltd | Structure of damper for moving blade of rotary machine |
GB9609721D0 (en) * | 1996-05-09 | 1996-07-10 | Rolls Royce Plc | Vibration damping |
JPH1193609A (en) * | 1997-09-17 | 1999-04-06 | Mitsubishi Heavy Ind Ltd | Gas turbine stationery blade |
DE50004724D1 (en) * | 1999-03-19 | 2004-01-22 | Siemens Ag | GAS TURBINE ROTOR WITH INTERIOR-COOLED GAS TURBINE BLADE |
US6371727B1 (en) * | 2000-06-05 | 2002-04-16 | The Boeing Company | Turbine blade tip shroud enclosed friction damper |
JP4495481B2 (en) * | 2004-02-18 | 2010-07-07 | イーグル・エンジニアリング・エアロスペース株式会社 | Sealing device |
US7575416B2 (en) * | 2006-05-18 | 2009-08-18 | United Technologies Corporation | Rotor assembly for a rotary machine |
FR2902843A1 (en) * | 2006-06-23 | 2007-12-28 | Snecma Sa | COMPRESSOR RECTIFIER AREA OR TURBOMACHINE DISTRIBUTOR SECTOR |
GB2449493B (en) | 2007-05-25 | 2009-08-12 | Rolls Royce Plc | Vibration damper assembly |
-
2009
- 2009-02-10 GB GB0902032A patent/GB2467582B/en not_active Expired - Fee Related
-
2010
- 2010-02-03 US US12/699,157 patent/US8596980B2/en not_active Expired - Fee Related
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2912223A (en) * | 1955-03-17 | 1959-11-10 | Gen Electric | Turbine bucket vibration dampener and sealing assembly |
GB1503453A (en) * | 1975-10-28 | 1978-03-08 | Europ Turb Vapeur | Rotor of a turbomachine |
US4815938A (en) * | 1987-12-24 | 1989-03-28 | Westinghouse Electric Corp. | Shroud gap control for integral shrouded blades |
JPH0539701A (en) * | 1991-08-06 | 1993-02-19 | Fuji Electric Co Ltd | Cascade of turbine moving blade |
US5984638A (en) * | 1994-08-12 | 1999-11-16 | Elliott Turbomachinery Co., Inc. | Turbomachine radial impeller vibration constraining and damping mechanism |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130052032A1 (en) * | 2010-01-26 | 2013-02-28 | Herakles | Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel |
US9188014B2 (en) * | 2010-01-26 | 2015-11-17 | Snecma | Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel |
EP2492449A1 (en) * | 2011-02-28 | 2012-08-29 | Alstom Technology Ltd | Sealing arrangement for a thermal machine |
CH704526A1 (en) * | 2011-02-28 | 2012-08-31 | Alstom Technology Ltd | Seal assembly for a thermal machine. |
US9255488B2 (en) | 2011-02-28 | 2016-02-09 | Alstom Technology Ltd. | Sealing arrangement for a thermal machine |
WO2015044699A1 (en) | 2013-09-26 | 2015-04-02 | Franco Tosi Meccanica S.P.A. | Rotor stage of axial turbine with an adaptive regulation to dynamic stresses |
Also Published As
Publication number | Publication date |
---|---|
US8596980B2 (en) | 2013-12-03 |
GB0902032D0 (en) | 2009-03-11 |
GB2467582B (en) | 2011-07-06 |
US20100202888A1 (en) | 2010-08-12 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20180210 |