GB2451568A - Seal tooth arrangement for gas turbine engine rotor blade tip shroud - Google Patents
Seal tooth arrangement for gas turbine engine rotor blade tip shroud Download PDFInfo
- Publication number
- GB2451568A GB2451568A GB0813750A GB0813750A GB2451568A GB 2451568 A GB2451568 A GB 2451568A GB 0813750 A GB0813750 A GB 0813750A GB 0813750 A GB0813750 A GB 0813750A GB 2451568 A GB2451568 A GB 2451568A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- seal tooth
- rotor blade
- seal
- tip shroud
- 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
- OQPDWFJSZHWILH-UHFFFAOYSA-N [Al].[Al].[Al].[Ti] Chemical compound [Al].[Al].[Al].[Ti] OQPDWFJSZHWILH-UHFFFAOYSA-N 0.000 claims description 3
- 229910021324 titanium aluminide Inorganic materials 0.000 claims description 3
- 230000001419 dependent effect Effects 0.000 claims 1
- 239000007789 gas Substances 0.000 description 14
- 239000000463 material Substances 0.000 description 7
- 239000000567 combustion gas Substances 0.000 description 6
- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- 229910000601 superalloy Inorganic materials 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
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A rotor blade 50 includes a tip shroud 62 having at least one seal tooth 80/86 disposed at an angle relative to the engine centerline when in an assembled condition, to the leading edge 77 of the tip shroud 62 and/or to the trailing edge 79 of the tip shroud 62. In another aspect, a rotor assembly comprises first and second rotors, a seal tooth 80/ 86 of a blade of a first rotor being offset relative to a blade 82/88 of a second rotor. A saw tooth pattern may be created to facilitate cutting into a surrounding honeycomb seal structure, in use.
Description
ROTOR BLADE
BACKGROUND OF THE INVENTION
The exemplary embodiments relate generally to gas turbine engine components and more specifically to rotor blades having tip shrouds.
Gas turbine engines typically include a compressor, a combustor, and at least one turbine. The compressor may compress air, which may be mixed with fuel and channeled to the combustor. The mixture may then be ignited for generating hot combustion gases, and the combustion gases may be channeled to the turbine. The turbine may extract energy from the combustion gases for powering the compressor, as well as producing useful work to propel an aircraft in flight or to power a load, such as an electrical generator.
The turbine may include a rotor assembly and a stator assembly. The rotor assembly may include a plurality of rotor blades extending radially outward from a disk. Each rotor blade may include an airfoil, which may extend between a platform and a tip.
Each rotor blade may also include a root that may extend below the platform and be received in a corresponding slot in the disk. Alternatively, the disk may be a blisk or bladed disk, which may alleviate the need for a root and the airfoil may extend directly from the disk. A combustion gas flowpath through the rotor assembly may be bound radially inward by the rotor blade platforms, and radially outward by a plurality of tip shrouds, wherein each tip shroud may include at least one seal tooth.
Typically, the at least one seal tooth may cooperate with a radially adjacent honeycomb to seal the flowpath. The at least one seal tooth may have at least one portion that is larger in cross section than the rest of the seal tooth. During forward motion of the blade relative to the honeycomb, this larger portion may engage with the honeycomb prior to the remainder of the seal tooth, and cut a wear track into the honeycomb. This may require the seal tooth to be non-axisymmetric.
Rotor blades can be made from a variety of materials. Some of these materials may allow the non-axisymmetric seal tooth to be cast into the final shape with little if any necessary machining. Other lower weight, lower cost or longer life materials, however, do not have the capability to be cast to a final shape and need to be machined. Machining of non-axisymmetric features with these materials can be time consuming and cause wasted material leading to longer production cycles.
BRIEF DESCRIPTION OF THE INVENTION
One exemplary embodiment may be directed to a rotor blade having a tip shroud having at least one seal tooth disposed at an angle relative to an engine centerline when in an assembled condition. In another exemplary embodiment, the seal tooth may be disposed at an angle relative to the leading and/or trailing edge.
BRIEF DESCRIPTION OF THE DRAWiNGS
Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings, in which: Figure 1 is a cross-sectional schematic view of an exemplary gas turbine engine.
Figure 2 is a partial cut-away cross-sectional view of an exemplary turbine assembly that may be used with a gas turbine engine, such as the gas turbine engine shown in Figure 1.
Figure 3 is a perspective view of a portion of an exemplary rotor blade that may be used with a gas turbine engine, such as the gas turbine engine shown in Figure 1.
Figure 4 is a top plan view of the rotor blade shown in Figure 3.
DETAILED DESCRIPTION OF THE INVENTION
Figure 1 is a schematic illustration of an exemplary gas turbine engine 10 including a fan assembly 12, a booster 14, a high pressure compressor 16, and a combustor 18.
The engine 10 also includes a high pressure turbine 20, and a low pressure turbine 22.
The fan assembly 12 includes an array of fan blades 24 extending radially outward from a rotor disk 26. The engine 10 has an intake side 28 and an exhaust side 30.
The engine 10 may be any gas turbine engine. For example, the engine 10 may be, but is not limited to being, a GE9O gas turbine engine available from General Electric Company, Cincinnati, Ohio. The fan assembly 12, booster 14, and turbine 22 may be coupled by a first rotor shaft 32, and the compressor 16 and turbine 20 may be coupled by a second rotor shaft 34.
In operation, air flows through the fan assembly 12 and compressed air is supplied to the high pressure compressor 16 through the booster 14. The highly compressed air is delivered to the combustor 18, where it is mixed with a fuel and ignited to generate combustion gases. The combustion gases are channeled from the combustor 18 to drive the turbines 20 and 22. The turbine 22 drives the fan assembly 12 and booster 14 by way of shaft 32. The turbine 20 drives the compressor 16 by way of shaft 34.
Figure 2 is a partial cut-away cross-sectional view of an exemplary rotating assembly that may be used with a gas turbine engine, such as, but not limited to, the gas turbine engine 10 (shown in Figure 1). In the exemplary embodiment, the rotor assembly 36 may be a turbine, such as, but not limited to, the low pressure turbine 20 (shown in Figure 1). However, the exemplary embodiments described and/or illustrated herein may be used with any rotor assembly. Rotor assembly 36 includes a plurality of rotors 38 joined together by couplings 40 about an axial centerline axis (not shown).
Each rotor 38 includes a rotor disk 42 including an annular radially outer rim 44, a radially inner hub 46, and an integral web 48 extending radially therebetween. Each rotor 38 also includes a plurality of blades 50 extending radially outwardly from the outer rim 44. One or more blades 50, of one or more rotors 40, may be integrally joined with respective rims 44. Moreover, one or more blades 50 of one or more rotors 40 may be removably joined to the respective rim 44 in a known manner using blade dovetails (not shown) which mount in complementary slots (not shown) in the respective rim 44.
Rotor blades 50 each include a leading edge 52, a trailing edge 54, and an airfoil 56 extending therebetween. Each airfoil 56 includes a suction side 58 and a circumferentially opposite pressure side 60. Suction and pressure sides 58 and 60, respectively, extend between axially spaced apart leading and trailing edges 52 and 54, respectively, and extend in radial span between a rotor blade tip shroud 62 and a rotor blade platform 64. A blade chord is measured between rotor blade leading and trailing edges 52 and 54, respectively. The radially outer surfaces 66 of the platforms 64 define a radially inner flowpath surface of rotor assembly 36 and the radially inner surfaces 68 of the blade tip shrouds 62 define a radially outer flowpath surface of rotor assembly 36.
Figure 3 is a perspective view of a portion of an exemplary rotor blade that may be used with a gas turbine engine, such as the gas turbine engine shown in Figure 1.
Figure 4 is a top plan view of the rotor blade shown in Figure 3. In one exemplary embodiment, the rotor blades 50 may include one or more seal teeth 70, which may be adjacent to and interact with a stator shroud 72. The one or more seal teeth 70 may be disposed within a cavity 74 defined by stator shroud 72 and rotor blade tip shroud 62.
The seal teeth 70 may cooperate with a radially adjacent honeycomb on the stator shroud 72 to seal the flowpath. The honeycomb may be disposed on the radially lower surface of the stator shroud 72. Although each blade tip shroud 62 is illustrated in Figures 2-4 as including two seal teeth 70 that each extend across an entire circumferential width of shroud 62 (shown in Figure 3), it should be noted that each tip shroud 62 may include any number of seal teeth 70 that may each extend across any portion of the circumferential width of shroud 62. Moreover, each tip shroud 62 may also include a pair of opposite interlock surfaces 76 and 78 that facilitate interlocking shrouds 62 of adjacent rotor blades 50 within a rotor 40. Each tip shroud 62 may include a leading edge 77 and a trailing edge 79.
As shown in Figures 3 and 4, the tip shroud 62 may include one or more seal teeth, such as seal tooth 80. The seal tooth 80 may be disposed at an angle such that a seal tooth 82 of an adjacent blade is offset from the seal tooth 80, thus creating a saw tooth' pattern at the blade-to-blade interface 84. The angle may be any angle so long as the seal tooth is not perpendicular to the engine centerline when in an assembled condition. The seal tooth may also be disposed at an angle relative to the leading edge 77 and/or trailing edge 79 of the tip shroud 80. The offset allows the seal tooth to have an effective' enlarged portion at the interface 84 so that the seal tooth 80 may appropriately cut into the honeycomb without having additional material. The offset may also allow the seal tooth 80 to be axisymmetric, which may be beneficial for manufacturing. The angle of the seal teeth 80 and 82 can be any appropriate angle such that one seal tooth is offset as to the adjacent seal tooth. In one exemplary embodiment, the seal tooth 80 and the seal tooth 82 may overlap at the interface 84.
In one exemplary embodiment, the tip shroud 62 may have an additional seal tooth 86. Similar to seal tooth 80, seal tooth 86 may be disposed at an angle such that a seal tooth 88 of an adjacent blade is offset from the seal tooth 86, thus creating the saw tooth pattern at the blade-to-blade interface 90. The angle of seal teeth 86 and 88 may be any appropriate angle such that one seal tooth is offset as to the adjacent seal tooth.
In one exemplary embodiment, seal teeth 80 and 82 may have the same angle as seal teeth 86 and 88, thus being parallel to each other. In another exemplary embodiment, seal teeth 80 and 82 may have an angle different from the angle of seal teeth 86 and 88.
The rotor blades and/or tip shrouds may be made of any material known in the art. In one exemplary embodiment, the blades and/or tip shrouds may be made from a nickel or cobalt-based superalloy. In another exemplary embodiment, the blades and/or tip shrouds may be made from a titanium alloy, such as, but not limited to titanium aluminide. In addition, the blade, tip shroud and/or seal teeth may be coated with any coating known in the art. In one exemplary embodiment, the blade and/or tip shroud may be coated with an environmental coating. The seal teeth may be coated with an abrasive coating, such as, but not limited to, aluminum oxide.
The blades and/or tip shrouds may be formed to their final shape or they may be formed and then machined to their final shape. In the event that the outer surface of the tip shroud needs to be machined, the use of an angled seal tooth may facilitate an axisymmetnc form for ease of machining, while allowing a feature to cut' the honeycomb. Typically, the tip shrouds may be machined on an arcuate path with the axis of rotation being the engine centerline. When the outer surface of the tip shroud is generally cylindrical (i.e. substantially parallel to the engine centerline in cross-section) then the axis of rotation of the arcuate path to create the outer surface may be the engine centerline rotated sufficiently to achieve the offset between adjacent seal teeth. If the outer surface is generally conical, the axis of rotation may need to be offset as well as angled relative to engine centerline. This may be required to ensure that the thickness at the edges of the tip shroud do not become undesirably thin or thick.
While this application has described various specific exemplary embodiments, those skilled in the art will recognize that those exemplary embodiments can be practiced with modification within the spirit and scope of the claims.
Claims (16)
- CLAIMS: 1. A rotor blade comprising: an airfoil; and a tip shroud extending from said airfoil, said tip shroud having at least one seal tooth disposed at an angle relative to an engine centerline when in an assembled condition.
- 2. A rotor blade comprising: an airfoil; and a tip shroud extending from said airfoil, said tip shroud having a leading edge, a trailing edge and at least one seal tooth, said at least one seal tooth disposed at an angle relative to the leading and/or trailing edge such that said at least one seal tooth is not parallel to said leading and/or trailing edge.
- 3. The rotor blade of claim 1 or claim 2, wherein said at least one seal tooth (80) is axisymmetric.
- 4. A rotor blade according to any one of the preceding claims, wherein said at least one seal tooth is not perpendicular to said engine centerline.
- 5. The rotor blade of any one of the preceding claims, wherein said tip shroud further comprises: a first interlocking surface; and a second interlocking surface.
- 6. The rotor blade of any one of the preceding claims, wherein said tip shroud further comprises: a second seal tooth disposed at an angle relative to an engine centerline when in an assembled condition.
- 7. The rotor blade of any one of the preceding claims, wherein said rotor blade is formed of titanium aluminide.
- 8. The rotor blade of claim 2 or any claim dependent upon claim 2, wherein said tip shroud further comprises: a second seal tooth disposed at an angle relative to said leading and/or trailing edge such that said a second seal tooth is not parallel to said leading and/or trailing edge.
- 9. A rotor assembly comprising: a rotor; a first rotor blade extending radially from said rotor having a first seal tooth; a second rotor blade extending radially from said rotor having a second seal tooth, said first and second seal teeth arranged so that said seal teeth are offset with respect to each other.
- 10. The rotor assembly of claim 9, wherein said first rotor blade is adjacent to said second rotor blade.
- 11. The rotor assembly of claim 9 or claim 10, wherein said first seal tooth and said second seal tooth overlap, creating a saw tooth pattern.
- 12. The rotor assembly of any one of claims 9 to 11, wherein said first and second seal teeth are axisymmetric.
- 13. The rotor assembly of any one of claims 9 to 12, further comprising: said first rotor blade having a third seal tooth that is axisymmetric and parallel to said first seal tooth; and said second rotor blade having a fourth seal tooth that is axisymnietric and parallel to said second seal tooth.
- 14. The rotor assembly of any one of claims 9 to 13, wherein said rotor blades are formed of titanium aluminide.
- 15. A rotor blade substantially as hereinbefore described with reference to the accompanying drawings.
- 16. A rotor assembly substantially as hereinbefore described with reference to the accompanying drawings.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/831,078 US20090097979A1 (en) | 2007-07-31 | 2007-07-31 | Rotor blade |
Publications (3)
Publication Number | Publication Date |
---|---|
GB0813750D0 GB0813750D0 (en) | 2008-09-03 |
GB2451568A true GB2451568A (en) | 2009-02-04 |
GB2451568B GB2451568B (en) | 2012-06-27 |
Family
ID=39747028
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB0813750.7A Expired - Fee Related GB2451568B (en) | 2007-07-31 | 2008-07-28 | Rotor blade |
Country Status (4)
Country | Link |
---|---|
US (1) | US20090097979A1 (en) |
JP (2) | JP5450997B2 (en) |
DE (1) | DE102008002944A1 (en) |
GB (1) | GB2451568B (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008061800A1 (en) * | 2008-12-11 | 2010-06-17 | Rolls-Royce Deutschland Ltd & Co Kg | Segmented sealing lips for labyrinth seals |
FR2967714A1 (en) * | 2010-11-22 | 2012-05-25 | Snecma | MOBILE AUB OF TURBOMACHINE |
EP2620653A1 (en) * | 2012-01-25 | 2013-07-31 | Rolls-Royce plc | A turbomachine casing assembly with blade containment cavity |
FR3001759A1 (en) * | 2013-02-07 | 2014-08-08 | Snecma | ROUGE AUBAGEE OF TURBOMACHINE |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009030566A1 (en) * | 2009-06-26 | 2010-12-30 | Mtu Aero Engines Gmbh | Shroud segment for placement on a bucket |
US20120195742A1 (en) * | 2011-01-28 | 2012-08-02 | Jain Sanjeev Kumar | Turbine bucket for use in gas turbine engines and methods for fabricating the same |
FR2985759B1 (en) * | 2012-01-17 | 2014-03-07 | Snecma | MOBILE AUB OF TURBOMACHINE |
US10597756B2 (en) | 2012-03-24 | 2020-03-24 | General Electric Company | Titanium aluminide intermetallic compositions |
KR102040958B1 (en) * | 2017-10-30 | 2019-11-05 | 두산중공업 주식회사 | Sealing structure of rotor and steam turbine having the same |
KR102011578B1 (en) * | 2017-11-09 | 2019-10-21 | 두산중공업 주식회사 | Cover structure of bucket and rotor and steamturbine having the same |
US11105209B2 (en) | 2018-08-28 | 2021-08-31 | General Electric Company | Turbine blade tip shroud |
US10907487B2 (en) | 2018-10-16 | 2021-02-02 | Honeywell International Inc. | Turbine shroud assemblies for gas turbine engines |
JP7389574B2 (en) * | 2019-06-28 | 2023-11-30 | 三菱重工航空エンジン株式会社 | aircraft gas turbine |
US11156110B1 (en) | 2020-08-04 | 2021-10-26 | General Electric Company | Rotor assembly for a turbine section of a gas turbine engine |
US11655719B2 (en) | 2021-04-16 | 2023-05-23 | General Electric Company | Airfoil assembly |
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GB1505534A (en) * | 1974-03-21 | 1978-03-30 | Maschf Augsburg Nuernberg Ag | Turbines and compressors |
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-
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- 2008-07-15 DE DE102008002944A patent/DE102008002944A1/en not_active Withdrawn
- 2008-07-23 JP JP2008189349A patent/JP5450997B2/en not_active Expired - Fee Related
- 2008-07-28 GB GB0813750.7A patent/GB2451568B/en not_active Expired - Fee Related
-
2013
- 2013-10-03 JP JP2013207847A patent/JP5576974B2/en not_active Expired - Fee Related
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GB1505534A (en) * | 1974-03-21 | 1978-03-30 | Maschf Augsburg Nuernberg Ag | Turbines and compressors |
JPS57102503A (en) * | 1980-12-17 | 1982-06-25 | Hitachi Ltd | Sealing structure for gap on tip of moving vane of turbine |
GB2298246A (en) * | 1995-02-23 | 1996-08-28 | Bmw Rolls Royce Gmbh | Turbine-blad-tip-sealing arrangement comprising a shroud band |
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Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008061800A1 (en) * | 2008-12-11 | 2010-06-17 | Rolls-Royce Deutschland Ltd & Co Kg | Segmented sealing lips for labyrinth seals |
US8251371B2 (en) | 2008-12-11 | 2012-08-28 | Rolls-Royce Deutschland Ltd Co KG | Segmented sealing lips for labyrinth sealing rings |
FR2967714A1 (en) * | 2010-11-22 | 2012-05-25 | Snecma | MOBILE AUB OF TURBOMACHINE |
WO2012069744A1 (en) * | 2010-11-22 | 2012-05-31 | Snecma | Turbomachine rotor blade and associated turbomachine |
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EP2620653A1 (en) * | 2012-01-25 | 2013-07-31 | Rolls-Royce plc | A turbomachine casing assembly with blade containment cavity |
FR3001759A1 (en) * | 2013-02-07 | 2014-08-08 | Snecma | ROUGE AUBAGEE OF TURBOMACHINE |
WO2014122403A1 (en) * | 2013-02-07 | 2014-08-14 | Snecma | Turbine engine impeller |
GB2525117A (en) * | 2013-02-07 | 2015-10-14 | Snecma | Turbine Engine Impeller |
GB2525117B (en) * | 2013-02-07 | 2017-01-11 | Snecma | Turbine Engine Impeller |
US10100658B2 (en) | 2013-02-07 | 2018-10-16 | Safran Aircraft Engines | Turbine engine impeller |
Also Published As
Publication number | Publication date |
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JP5576974B2 (en) | 2014-08-20 |
GB2451568B (en) | 2012-06-27 |
JP2009036203A (en) | 2009-02-19 |
GB0813750D0 (en) | 2008-09-03 |
US20090097979A1 (en) | 2009-04-16 |
JP2013256961A (en) | 2013-12-26 |
DE102008002944A1 (en) | 2009-02-05 |
JP5450997B2 (en) | 2014-03-26 |
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