US20100232939A1 - Machine Seal Assembly - Google Patents
Machine Seal Assembly Download PDFInfo
- Publication number
- US20100232939A1 US20100232939A1 US12/402,808 US40280809A US2010232939A1 US 20100232939 A1 US20100232939 A1 US 20100232939A1 US 40280809 A US40280809 A US 40280809A US 2010232939 A1 US2010232939 A1 US 2010232939A1
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- US
- United States
- Prior art keywords
- seal
- wheel
- machine
- bucket
- coverplate
- 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.)
- Abandoned
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Classifications
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- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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- 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
- F05D2240/00—Components
- F05D2240/55—Seals
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- 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
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/57—Leaf seals
Definitions
- the subject matter disclosed herein relates generally to machines and a seal assembly for machines and more specifically to a seal assembly to improve the operation, performance and efficiency of a machine.
- Machine performance is degraded by the loss of pressurized cooling air and ingestion of hot gas flow.
- a first aspect of the invention provides a machine comprising: a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel, and a seal that extends along a side of the bucket and the wheel, covering an interface there between.
- a second aspect of the invention provides a seal assembly for a machine having a rotating shaft, the seal assembly comprising: a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel; and a seal that extends along a side of the bucket and the wheel, covering an interface there between.
- FIG. 1 shows a cross-sectional view of a bucket and wheel from a machine.
- FIG. 2 shows a cross-sectional view of a bucket and wheel from a machine with an enlarged view from an area of FIG. 1 illustrating a coverplate and seal.
- FIG. 3 shows a cross-sectional view of a machine showing gas and air flow movement.
- FIG. 4 shows a 360-degree single coil seal with a single split.
- FIG. 5 shows a 360-degree single coil seal with a single split wherein the ends of the split are mechanically coupled and there is a segmented coverplate over the mechanically coupled ends of the single coil seal.
- FIG. 6 shows a 720-degree multi-coil seal.
- FIG. 7 shows a portion of a segmented seal.
- FIG. 8 shows a portion of a segmented seal with a segmented coverplate over the segmented seal.
- FIG. 9 shows a cross sectional view of a bucket and wheel from a machine.
- the invention discussed herein includes a coverplate that is fastened to a wheel and bucket of a machine and a seal positioned between the coverplate and the wheel and the bucket.
- a coverplate and seal on the machine is that it reduces the loss of pressurized air from the system.
- the coverplate and seal may prevent the inflow of hot gas into the wheelspace and aid in the secondary air flow of the machine.
- the coverplate and seal discussed herein may facilitate maintenance on the machine.
- coverplate and seal may facilitate assembly and disassembly of the machine as the coverplate and seal can be installed and removed while the rotating shaft is on the half shell.
- the coverplate and seal may also improve the machine's performance by acting as a heat shield and reduce vibration through the addition of damping.
- the coverplate and seal can be installed on a forward side or an aft side of the wheel. Alternatively, the coverplate and seal can be installed on the forward side and the aft side of the wheel.
- FIG. 1 shows a cross-sectional view of a relevant portion of a machine 100 including seal assembly 101 .
- Machine 100 includes a bucket 102 , a wheel 104 and a rotating shaft 106 .
- at least one wheel 104 is coupled to rotating shaft 106 of machine 100 .
- Each wheel 104 may include a plurality of buckets 102 upon which gas acts to turn rotating shaft 106 .
- FIG. 2 shows an enlarged view of a relevant portion of FIG. 1 .
- Seal assembly 101 includes a seal 108 , a coverplate 110 and an angel wing 112 .
- coverplate 110 fastens to wheel 104 of machine 100 using a hook 206 .
- Alternative embodiments for fastening coverplate 110 to wheel 104 may include, for example: a bolt, a pin, a stack or a bayonet retaining ring.
- coverplate 110 can include an outer edge 208 that engages a slot 210 in bucket 102 of machine 100 .
- FIG. 3 shows a cross-sectional view of machine 100 showing gas and air flow movement.
- FIG. 3 shows a nozzle 302 of machine 100 .
- nozzle 302 is located on both sides of bucket 102 . It is understood, however, that nozzle 302 would be present only on a forward side of bucket 102 where the bucket is a last stage bucket.
- a hot gas flow 308 moves across bucket 102 .
- nozzle support ring 304 Immediately below nozzle 302 on the forward (left) or upstream side of machine 100 is a nozzle support ring 304 .
- a diaphragm 306 Immediately below nozzle 302 on the aft (right) or downstream side of machine 100 is a diaphragm 306 .
- Nozzle 302 includes on both the forward and aft sides, a part 305 that extends from nozzle 302 towards wheel 104 .
- a wheelspace 314 exists on the forward and aft side of bucket 102 .
- wheelspace 314 is between nozzle supporting ring 304 and wheel 104 .
- wheelspace 314 is between diaphragm 306 and wheel 104 .
- Wheelspace purge air 312 moves through wheelspace 314 . Additionally, bucket supply cooling air (not shown) moves from wheel 104 towards bucket 102 . An illustration of the movement of wheelspace purge air 312 is shown as it moves through wheelspace 314 and across wheel 104 .
- Coverplate 110 aids in reducing the amount of wheelspace purge air 312 that is able to move between wheel 104 and nozzle support ring 304 on the forward side and wheel 104 and diaphragm 306 on the aft side. Additionally, coverplate 110 aids in the bucket supply cooling air reaching bucket 102 and not entering wheelspace 314 . As described above, in one embodiment coverplate 110 and seal 108 can be installed on a forward side or an aft side of wheel 104 ( FIG. 1 ).
- coverplate 110 and seal 108 can be installed on the forward side and the aft side of wheel 104 .
- Angel wing 112 may aid in preventing the hot flowpath gas from entering wheelspace 314 .
- wheelspace purge air 312 is able to enter perforation 316 in wheel 104 .
- coverplate 110 and seal 108 it may reduce or eliminate the amount of wheelspace purge air 312 entering or moving through wheel 104 into wheelspace 314 .
- wheelspace purge air 310 would be able to move between wheel 104 and wheelspace 314 .
- Coverplate 110 and seal 108 aid in preventing the loss of wheelspace purge air 312 .
- bucket supply cooling air may enter wheelspace 314 .
- coverplate 110 may be segmented.
- seal 108 may be segmented.
- both coverplate 110 and seal 108 may be segmented.
- seal 108 is positioned to overlap an interface 804 on segment coverplate 806 to eliminate a gap between adjacent circumferentially positioned coverplate segments 802 .
- Coverplate 110 and seal 108 can also be used to aid in the secondary flow design of machine 100 .
- coverplate 110 and seal 108 can be installed and positioned to aid in the movement of air and gas flow to directed locations.
- coverplate 110 and seal 108 can be installed and positioned to prevent leakages of pressurized air (e.g., wheelspace purge air and bucket supply cooling air) and ingestion of hot gas.
- coverplate 110 and seal 108 can be used as a heat shield for wheel 104 by reducing the amount of hot gas flow 308 that contacts or comes in proximity to wheel 104 or by providing an additional barrier between bucket 102 and wheel 104 .
- coverplate 110 and seal 108 can be used to dampen vibration on wheel 104 and bucket 102 and for machine 100 as a whole.
- coverplate 110 and seal 108 can provide an additional mechanical connection between wheel 104 and bucket 102 .
- the additional connection between bucket 102 and wheel 104 may provide increased rigidity and reduce the vibration while machine 100 is in operation.
- a 360-degree single coil seal with a single split (“single coil seal”) 402 is shown.
- the single coil seal 402 allows for installation and maintenance, including assembly and disassembly, on machine 100 both at the factory and when machine 100 is at a customer's site.
- the single coil seal 402 allows for the seal to be spread apart allowing for maintenance and repair of machine 100 .
- by single coil seal 402 having a break in its circumference it provides the flexibility so that it may be maneuvered on and off of machine 100 .
- single coil seal 402 with its single split retains the rigidity and durability where it can perform as described in detail above, and be installed and removed from machine 100 .
- single coil seal 502 can be mechanically coupled by, for example, a tongue and groove, a lap joint, a dovetail, a butt joint, a weld or a braze. Additionally, a coverplate 504 can be placed over the joint in the single coil seal 502 when it is mechanically coupled. In one embodiment, a mechanically coupled single coil seal with a coverplate 504 will have the single coil seal 402 positioned on the coverplate 504 to eliminate a gap 506 between adjacent circumferentially positioned coverplate segments 504 .
- FIG. 6 illustrates a 720-degree multi coil seal (“multi coil seal”) 602 .
- the ends of the multi coil seal are not mechanically coupled to one another. This allows for flexibility in the seal during installation and maintenance of machine 100 in addition to installation and removal of multi coil seal 602 on machine 100 .
- Other embodiments may include a multi coil seal having more than 720 degrees, if desired.
- Segmented seal 700 includes a joint 702 where segments 704 connect.
- a coverplate 110 can be installed over a segmented seal 700 .
- FIG. 8 shows a segmented seal 700 with a segmented coverplate 806 over segmented seal 700 .
- a coverplate joint 804 can be staggered from joint 702 of segmented seal 700 where the segmented seal 700 is positioned on the coverplate segment 804 to eliminate a gap between adjacent circumferentially positioned coverplate segments.
- FIG. 9 this figure illustrates an alternative embodiment wherein a seal 904 extends along a side of bucket 102 and wheel 104 covering an interface therebetween.
- Seal 904 may attach to bucket 102 by a hook 902 on bucket 102 and seal 904 may attach to wheel 104 by a hook 906 on wheel 104 .
- Seal 904 may be on the forward or aft side of wheel 104 .
- seal 904 may be may be on the forward and aft side of wheel 104 .
- Seal 904 may take the form of any of the above-described seals.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A machine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a seal that extends along a side of the bucket and the wheel, covering an interface there between.
Description
- The current application is related to U.S. patent application Ser. No. ______, titled “GAS TURBINE HAVING SEAL ASSEMBLY WITH COVERPLATE AND SEAL,” filed on Mar. —, 2009.
- The subject matter disclosed herein relates generally to machines and a seal assembly for machines and more specifically to a seal assembly to improve the operation, performance and efficiency of a machine. Machine performance is degraded by the loss of pressurized cooling air and ingestion of hot gas flow.
- A machine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising: a seal that extends along a side of the bucket and the wheel, covering an interface there between.
- A first aspect of the invention provides a machine comprising: a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel, and a seal that extends along a side of the bucket and the wheel, covering an interface there between.
- A second aspect of the invention provides a seal assembly for a machine having a rotating shaft, the seal assembly comprising: a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel; and a seal that extends along a side of the bucket and the wheel, covering an interface there between.
- These and other features of the disclosure will be more readily understood from the following detailed description of the various aspects of the invention taken in conjunction with the accompanying drawings that depict various aspects of the invention, in which:
-
FIG. 1 shows a cross-sectional view of a bucket and wheel from a machine. -
FIG. 2 shows a cross-sectional view of a bucket and wheel from a machine with an enlarged view from an area ofFIG. 1 illustrating a coverplate and seal. -
FIG. 3 shows a cross-sectional view of a machine showing gas and air flow movement. -
FIG. 4 shows a 360-degree single coil seal with a single split. -
FIG. 5 shows a 360-degree single coil seal with a single split wherein the ends of the split are mechanically coupled and there is a segmented coverplate over the mechanically coupled ends of the single coil seal. -
FIG. 6 shows a 720-degree multi-coil seal. -
FIG. 7 shows a portion of a segmented seal. -
FIG. 8 shows a portion of a segmented seal with a segmented coverplate over the segmented seal. -
FIG. 9 shows a cross sectional view of a bucket and wheel from a machine. - It is noted that the drawings are not to scale. The drawings are intended to depict only typical aspects of the invention, and therefore should not be considered as limiting the scope of the invention. In the drawings, like numbering represents like elements between the drawings.
- As indicated above, aspects of the invention provide improved operation, performance and efficiency of a machine. As used throughout this application, reference to machine is to include: a gas turbine, a steam turbine or a compressor. In one embodiment, the invention discussed herein includes a coverplate that is fastened to a wheel and bucket of a machine and a seal positioned between the coverplate and the wheel and the bucket. One feature of the coverplate and seal on the machine is that it reduces the loss of pressurized air from the system. Additionally, the coverplate and seal may prevent the inflow of hot gas into the wheelspace and aid in the secondary air flow of the machine. Moreover, the coverplate and seal discussed herein may facilitate maintenance on the machine. Furthermore, the coverplate and seal may facilitate assembly and disassembly of the machine as the coverplate and seal can be installed and removed while the rotating shaft is on the half shell. The coverplate and seal may also improve the machine's performance by acting as a heat shield and reduce vibration through the addition of damping. The coverplate and seal can be installed on a forward side or an aft side of the wheel. Alternatively, the coverplate and seal can be installed on the forward side and the aft side of the wheel.
- Turning to the drawings,
FIG. 1 shows a cross-sectional view of a relevant portion of amachine 100 includingseal assembly 101.Machine 100 includes abucket 102, awheel 104 and a rotatingshaft 106. As understood, at least onewheel 104 is coupled to rotatingshaft 106 ofmachine 100. Eachwheel 104 may include a plurality ofbuckets 102 upon which gas acts to turn rotatingshaft 106. -
FIG. 2 shows an enlarged view of a relevant portion ofFIG. 1 .Seal assembly 101 includes aseal 108, acoverplate 110 and anangel wing 112. In one embodiment,coverplate 110 fastens towheel 104 ofmachine 100 using ahook 206. Alternative embodiments for fasteningcoverplate 110 towheel 104 may include, for example: a bolt, a pin, a stack or a bayonet retaining ring. In another embodiment,coverplate 110 can include anouter edge 208 that engages aslot 210 inbucket 102 ofmachine 100. -
FIG. 3 shows a cross-sectional view ofmachine 100 showing gas and air flow movement.FIG. 3 shows anozzle 302 ofmachine 100. As illustrated,nozzle 302 is located on both sides ofbucket 102. It is understood, however, thatnozzle 302 would be present only on a forward side ofbucket 102 where the bucket is a last stage bucket. Ahot gas flow 308 moves acrossbucket 102. Immediately belownozzle 302 on the forward (left) or upstream side ofmachine 100 is anozzle support ring 304. Immediately belownozzle 302 on the aft (right) or downstream side ofmachine 100 is adiaphragm 306.Nozzle 302 includes on both the forward and aft sides, apart 305 that extends fromnozzle 302 towardswheel 104. Awheelspace 314 exists on the forward and aft side ofbucket 102. On the forward side,wheelspace 314 is betweennozzle supporting ring 304 andwheel 104. On the aft side,wheelspace 314 is betweendiaphragm 306 andwheel 104. -
Wheelspace purge air 312 moves throughwheelspace 314. Additionally, bucket supply cooling air (not shown) moves fromwheel 104 towardsbucket 102. An illustration of the movement ofwheelspace purge air 312 is shown as it moves throughwheelspace 314 and acrosswheel 104. Coverplate 110 aids in reducing the amount ofwheelspace purge air 312 that is able to move betweenwheel 104 andnozzle support ring 304 on the forward side andwheel 104 anddiaphragm 306 on the aft side. Additionally, coverplate 110 aids in the bucket supply coolingair reaching bucket 102 and not enteringwheelspace 314. As described above, in oneembodiment coverplate 110 andseal 108 can be installed on a forward side or an aft side of wheel 104 (FIG. 1 ). In another embodiment,coverplate 110 andseal 108 can be installed on the forward side and the aft side ofwheel 104. Additionally, there may be one ormore angel wings 112 oncoverplate 110. Angelwing 112 may aid in preventing the hot flowpath gas from enteringwheelspace 314. - When there is no
coverplate 110 andseal 108 present,wheelspace purge air 312 is able to enterperforation 316 inwheel 104. When coverplate 110 and seal 108 are present, it may reduce or eliminate the amount ofwheelspace purge air 312 entering or moving throughwheel 104 intowheelspace 314. If nocoverplate 110 and seal 108 are installed,wheelspace purge air 310 would be able to move betweenwheel 104 andwheelspace 314.Coverplate 110 and seal 108 aid in preventing the loss ofwheelspace purge air 312. Moreover, when there is nocoverplate 110 and seal 108 present, bucket supply cooling air may enterwheelspace 314. - In one embodiment,
coverplate 110 may be segmented. In another embodiment, seal 108 may be segmented. In a further embodiment, bothcoverplate 110 and seal 108 may be segmented. In an alternative embodiment, shown inFIG. 8 , where there is asegmented coverplate 806 and asegmented seal 700 or eithersegmented coverplate 806 orsegmented seal 700,seal 108 is positioned to overlap aninterface 804 onsegment coverplate 806 to eliminate a gap between adjacent circumferentially positionedcoverplate segments 802. -
Coverplate 110 and seal 108 can also be used to aid in the secondary flow design ofmachine 100. Specifically,coverplate 110 and seal 108 can be installed and positioned to aid in the movement of air and gas flow to directed locations. Moreover,coverplate 110 and seal 108 can be installed and positioned to prevent leakages of pressurized air (e.g., wheelspace purge air and bucket supply cooling air) and ingestion of hot gas. Additionally,coverplate 110 and seal 108 can be used as a heat shield forwheel 104 by reducing the amount ofhot gas flow 308 that contacts or comes in proximity towheel 104 or by providing an additional barrier betweenbucket 102 andwheel 104. In a further embodiment,coverplate 110 and seal 108 can be used to dampen vibration onwheel 104 andbucket 102 and formachine 100 as a whole. For example,coverplate 110 and seal 108 can provide an additional mechanical connection betweenwheel 104 andbucket 102. The additional connection betweenbucket 102 andwheel 104 may provide increased rigidity and reduce the vibration whilemachine 100 is in operation. - Turning to
FIG. 4 , a 360-degree single coil seal with a single split (“single coil seal”) 402 is shown. The single coil seal 402 allows for installation and maintenance, including assembly and disassembly, onmachine 100 both at the factory and whenmachine 100 is at a customer's site. In one embodiment, the single coil seal 402 allows for the seal to be spread apart allowing for maintenance and repair ofmachine 100. In a further embodiment, by single coil seal 402 having a break in its circumference, it provides the flexibility so that it may be maneuvered on and off ofmachine 100. In another embodiment, single coil seal 402 with its single split retains the rigidity and durability where it can perform as described in detail above, and be installed and removed frommachine 100. - Turning to
FIG. 5 , and with continuing reference toFIG. 4 , the ends of single coil seal 502 can be mechanically coupled by, for example, a tongue and groove, a lap joint, a dovetail, a butt joint, a weld or a braze. Additionally, a coverplate 504 can be placed over the joint in the single coil seal 502 when it is mechanically coupled. In one embodiment, a mechanically coupled single coil seal with a coverplate 504 will have the single coil seal 402 positioned on the coverplate 504 to eliminate a gap 506 between adjacent circumferentially positioned coverplate segments 504. -
FIG. 6 illustrates a 720-degree multi coil seal (“multi coil seal”) 602. In one embodiment, the ends of the multi coil seal are not mechanically coupled to one another. This allows for flexibility in the seal during installation and maintenance ofmachine 100 in addition to installation and removal of multi coil seal 602 onmachine 100. Other embodiments may include a multi coil seal having more than 720 degrees, if desired. - Turning to
FIG. 7 , a portion of asegmented seal 700 is illustrated.Segmented seal 700 includes a joint 702 wheresegments 704 connect. In one embodiment, acoverplate 110 can be installed over asegmented seal 700.FIG. 8 shows asegmented seal 700 with asegmented coverplate 806 oversegmented seal 700. ExaminingFIG. 8 , with continuing reference toFIG. 7 , in one embodiment a coverplate joint 804 can be staggered from joint 702 ofsegmented seal 700 where thesegmented seal 700 is positioned on thecoverplate segment 804 to eliminate a gap between adjacent circumferentially positioned coverplate segments. - Turning to
FIG. 9 , this figure illustrates an alternative embodiment wherein aseal 904 extends along a side ofbucket 102 andwheel 104 covering an interface therebetween.Seal 904 may attach tobucket 102 by ahook 902 onbucket 102 and seal 904 may attach towheel 104 by ahook 906 onwheel 104.Seal 904 may be on the forward or aft side ofwheel 104. In an additional embodiment, seal 904 may be may be on the forward and aft side ofwheel 104.Seal 904 may take the form of any of the above-described seals. - While various embodiments are described herein, it will be appreciated from the specification that various combinations of elements, variations or improvements therein may be made by those skilled in the art, and are within the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (18)
1. A machine comprising:
a rotating shaft;
a wheel coupled to the rotating shaft;
a bucket coupled to the wheel; and
a seal that extends along a side of the bucket and the wheel, covering an interface therebetween.
2. The machine of claim 1 , wherein the bucket includes a hook for fastening the seal to the bucket of the machine.
3. The machine of claim 1 , wherein the wheel includes a hook for fastening the seal to the wheel of the machine.
4. The machine of claim 1 , wherein the seal includes a 360-degree seal with a single split.
5. The machine of claim 1 , wherein the seal includes a 720-degree multi-coil seal.
6. The machine of claim 1 , wherein the seal includes a segmented seal.
7. The machine of claim 1 , wherein the seal is installed on a forward side of the wheel.
8. The machine of claim 1 , wherein the seal is installed on an aft side of the wheel.
9. The machine of claim 1 , wherein the seal is installed on the forward side and the aft side of the wheel.
10. A seal assembly for a machine having a rotating shaft, the seal assembly comprising:
a wheel coupled to the rotating shaft;
a bucket coupled to the wheel; and
a seal that extends along a side of the bucket and the wheel, covering an interface therebetween.
11. The seal assembly of claim 10 , wherein the bucket includes a hook for fastening the seal to the bucket of the machine.
12. The seal assembly of claim 10 , wherein the wheel includes a hook for fastening the seal to the wheel of the machine.
13. The seal assembly of claim 10 , wherein the seal includes a 360-degree seal with a single split.
14. The seal assembly of claim 10 , wherein the seal includes a 720-degree multi-coil seal.
15. The seal assembly of claim 10 , wherein the seal includes a segmented seal.
16. The seal assembly of claim 10 , wherein the seal is installed on a forward side of the wheel.
17. The seal assembly of claim 10 , wherein the seal is installed on an aft side of the wheel.
18. The seal assembly of claim 10 , wherein the seal is installed on the forward side and the aft side of the wheel.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
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US12/402,808 US20100232939A1 (en) | 2009-03-12 | 2009-03-12 | Machine Seal Assembly |
EP10155312.1A EP2236768A3 (en) | 2009-03-12 | 2010-03-03 | Turbomachine seal assembly |
JP2010052474A JP5475511B2 (en) | 2009-03-12 | 2010-03-10 | Mechanical seal assembly |
CN2010101468881A CN101893001A (en) | 2009-03-12 | 2010-03-12 | Turbomachine seal assembly |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/402,808 US20100232939A1 (en) | 2009-03-12 | 2009-03-12 | Machine Seal Assembly |
Publications (1)
Publication Number | Publication Date |
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US20100232939A1 true US20100232939A1 (en) | 2010-09-16 |
Family
ID=42337449
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US12/402,808 Abandoned US20100232939A1 (en) | 2009-03-12 | 2009-03-12 | Machine Seal Assembly |
Country Status (4)
Country | Link |
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US (1) | US20100232939A1 (en) |
EP (1) | EP2236768A3 (en) |
JP (1) | JP5475511B2 (en) |
CN (1) | CN101893001A (en) |
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US20100239413A1 (en) * | 2009-03-23 | 2010-09-23 | General Electric Company | Apparatus for turbine engine cooling air management |
US20100239414A1 (en) * | 2009-03-23 | 2010-09-23 | General Electric Company | Apparatus for turbine engine cooling air management |
US20130094969A1 (en) * | 2011-10-17 | 2013-04-18 | General Electric Company | System for sealing a shaft |
US8845284B2 (en) | 2010-07-02 | 2014-09-30 | General Electric Company | Apparatus and system for sealing a turbine rotor |
US8864453B2 (en) | 2012-01-20 | 2014-10-21 | General Electric Company | Near flow path seal for a turbomachine |
US9080456B2 (en) | 2012-01-20 | 2015-07-14 | General Electric Company | Near flow path seal with axially flexible arms |
US9217334B2 (en) | 2011-10-26 | 2015-12-22 | General Electric Company | Turbine cover plate assembly |
US20170107837A1 (en) * | 2015-10-20 | 2017-04-20 | General Electric Company | Turbine slotted arcuate leaf seal |
US10337344B2 (en) * | 2014-05-27 | 2019-07-02 | Siemens Aktiengesellschaft | Turbomachine with an ingestion shield and use of the turbomachine |
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FR2999641B1 (en) * | 2012-12-17 | 2014-12-26 | Snecma | TURBOMACHINE FLOOR |
EP3438410B1 (en) | 2017-08-01 | 2021-09-29 | General Electric Company | Sealing system for a rotary machine |
FI129562B (en) * | 2019-06-24 | 2022-04-29 | Flaektgroup Sweden Ab | Method of forming a sealing between ventilation pipes and/or terminals thereof, and sealing |
Citations (55)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3043562A (en) * | 1961-04-10 | 1962-07-10 | Gen Electric | Combination sealing and restraining member for long-shank turbo-machine buckets |
US3137478A (en) * | 1962-07-11 | 1964-06-16 | Gen Electric | Cover plate assembly for sealing spaces between turbine buckets |
US3501249A (en) * | 1968-06-24 | 1970-03-17 | Westinghouse Electric Corp | Side plates for turbine blades |
US3751183A (en) * | 1971-12-02 | 1973-08-07 | Gen Electric | Interblade baffle and damper |
US3768924A (en) * | 1971-12-06 | 1973-10-30 | Gen Electric | Boltless blade and seal retainer |
US3814539A (en) * | 1972-10-04 | 1974-06-04 | Gen Electric | Rotor sealing arrangement for an axial flow fluid turbine |
US3829233A (en) * | 1973-06-27 | 1974-08-13 | Westinghouse Electric Corp | Turbine diaphragm seal structure |
US3853425A (en) * | 1973-09-07 | 1974-12-10 | Westinghouse Electric Corp | Turbine rotor blade cooling and sealing system |
US4019833A (en) * | 1974-11-06 | 1977-04-26 | Rolls-Royce (1971) Limited | Means for retaining blades to a disc or like structure |
US4021138A (en) * | 1975-11-03 | 1977-05-03 | Westinghouse Electric Corporation | Rotor disk, blade, and seal plate assembly for cooled turbine rotor blades |
US4088421A (en) * | 1976-09-30 | 1978-05-09 | General Electric Company | Coverplate damping arrangement |
US4218189A (en) * | 1977-08-09 | 1980-08-19 | Rolls-Royce Limited | Sealing means for bladed rotor for a gas turbine engine |
US4265594A (en) * | 1978-03-02 | 1981-05-05 | Bbc Brown Boveri & Company Limited | Turbine blade having heat localization segments |
US4326835A (en) * | 1979-10-29 | 1982-04-27 | General Motors Corporation | Blade platform seal for ceramic/metal rotor assembly |
US4480958A (en) * | 1983-02-09 | 1984-11-06 | The United States Of America As Represented By The Secretary Of The Air Force | High pressure turbine rotor two-piece blade retainer |
US4500098A (en) * | 1983-12-22 | 1985-02-19 | United Technologies Corporation | Gas seal for rotating components |
US4507052A (en) * | 1983-03-31 | 1985-03-26 | General Motors Corporation | End seal for turbine blade bases |
US4523890A (en) * | 1983-10-19 | 1985-06-18 | General Motors Corporation | End seal for turbine blade base |
US4645424A (en) * | 1984-07-23 | 1987-02-24 | United Technologies Corporation | Rotating seal for gas turbine engine |
US4659285A (en) * | 1984-07-23 | 1987-04-21 | United Technologies Corporation | Turbine cover-seal assembly |
US4659289A (en) * | 1984-07-23 | 1987-04-21 | United Technologies Corporation | Turbine side plate assembly |
US4743164A (en) * | 1986-12-29 | 1988-05-10 | United Technologies Corporation | Interblade seal for turbomachine rotor |
US4781534A (en) * | 1987-02-27 | 1988-11-01 | Westinghouse Electric Corp. | Apparatus and method for reducing windage and leakage in steam turbine incorporating axial entry blade |
US5222742A (en) * | 1990-12-22 | 1993-06-29 | Rolls-Royce Plc | Seal arrangement |
US5236302A (en) * | 1991-10-30 | 1993-08-17 | General Electric Company | Turbine disk interstage seal system |
US5257909A (en) * | 1992-08-17 | 1993-11-02 | General Electric Company | Dovetail sealing device for axial dovetail rotor blades |
US5275534A (en) * | 1991-10-30 | 1994-01-04 | General Electric Company | Turbine disk forward seal assembly |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
US5338154A (en) * | 1993-03-17 | 1994-08-16 | General Electric Company | Turbine disk interstage seal axial retaining ring |
US5429478A (en) * | 1994-03-31 | 1995-07-04 | United Technologies Corporation | Airfoil having a seal and an integral heat shield |
US5503528A (en) * | 1993-12-27 | 1996-04-02 | Solar Turbines Incorporated | Rim seal for turbine wheel |
US5803710A (en) * | 1996-12-24 | 1998-09-08 | United Technologies Corporation | Turbine engine rotor blade platform sealing and vibration damping device |
US5954477A (en) * | 1996-09-26 | 1999-09-21 | Rolls-Royce Plc | Seal plate |
US5967745A (en) * | 1997-03-18 | 1999-10-19 | Mitsubishi Heavy Industries, Ltd. | Gas turbine shroud and platform seal system |
US5993160A (en) * | 1997-12-11 | 1999-11-30 | Pratt & Whitney Canada Inc. | Cover plate for gas turbine rotor |
US6086329A (en) * | 1997-03-12 | 2000-07-11 | Mitsubishi Heavy Industries, Ltd. | Seal plate for a gas turbine moving blade |
US6106234A (en) * | 1997-12-03 | 2000-08-22 | Rolls-Royce Plc | Rotary assembly |
US6120249A (en) * | 1994-10-31 | 2000-09-19 | Siemens Westinghouse Power Corporation | Gas turbine blade platform cooling concept |
US6189891B1 (en) * | 1997-03-12 | 2001-02-20 | Mitsubishi Heavy Industries, Ltd. | Gas turbine seal apparatus |
US6190131B1 (en) * | 1999-08-31 | 2001-02-20 | General Electric Co. | Non-integral balanced coverplate and coverplate centering slot for a turbine |
US6220814B1 (en) * | 1998-07-16 | 2001-04-24 | Siemens Westinghouse Power Corporation | Turbine interstage sealing arrangement |
US6273683B1 (en) * | 1999-02-05 | 2001-08-14 | Siemens Westinghouse Power Corporation | Turbine blade platform seal |
US6315298B1 (en) * | 1999-11-22 | 2001-11-13 | United Technologies Corporation | Turbine disk and blade assembly seal |
US6506016B1 (en) * | 2001-11-15 | 2003-01-14 | General Electric Company | Angel wing seals for blades of a gas turbine and methods for determining angel wing seal profiles |
US6561764B1 (en) * | 1999-03-19 | 2003-05-13 | Siemens Aktiengesellschaft | Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms |
US6776573B2 (en) * | 2000-11-30 | 2004-08-17 | Snecma Moteurs | Bladed rotor disc side-plate and corresponding arrangement |
US6945749B2 (en) * | 2003-09-12 | 2005-09-20 | Siemens Westinghouse Power Corporation | Turbine blade platform cooling system |
US20060021218A1 (en) * | 2002-08-23 | 2006-02-02 | Mcmillan Alison J | Seals and a method of making seals |
US7121800B2 (en) * | 2004-09-13 | 2006-10-17 | United Technologies Corporation | Turbine blade nested seal damper assembly |
US7189055B2 (en) * | 2005-05-31 | 2007-03-13 | Pratt & Whitney Canada Corp. | Coverplate deflectors for redirecting a fluid flow |
US7241109B2 (en) * | 2004-06-04 | 2007-07-10 | Rolls-Royce Plc | Seal system |
US7264448B2 (en) * | 2004-10-06 | 2007-09-04 | Siemens Power Corporation, Inc. | Remotely accessible locking system for turbine blades |
US7264447B2 (en) * | 2003-12-05 | 2007-09-04 | Honda Motor Co., Ltd. | Sealing arrangement for an axial turbine wheel |
US20070258816A1 (en) * | 2005-09-26 | 2007-11-08 | Pratt & Whitney Canada Corp. | Blades for a gas turbine engine with integrated sealing plate and method |
US20100196164A1 (en) * | 2009-02-05 | 2010-08-05 | General Electric Company | Turbine Coverplate Systems |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1291302A (en) * | 1970-03-14 | 1972-10-04 | Sec Dep For Defendence | Improvements in bladed rotor assemblies |
JPS61205303A (en) * | 1985-03-06 | 1986-09-11 | Mitsubishi Heavy Ind Ltd | Stopper in axial direction for turbine moving blade |
JPH0723524Y2 (en) * | 1988-03-29 | 1995-05-31 | 川崎重工業株式会社 | Axial turbine |
US6669443B2 (en) * | 2001-11-16 | 2003-12-30 | General Electric Company | Rotor platform modification and methods using brush seals in diaphragm packing area of steam turbines to eliminate rotor bowing |
US6884028B2 (en) * | 2002-09-30 | 2005-04-26 | General Electric Company | Turbomachinery blade retention system |
US6779972B2 (en) * | 2002-10-31 | 2004-08-24 | General Electric Company | Flowpath sealing and streamlining configuration for a turbine |
JP2006009576A (en) * | 2004-06-22 | 2006-01-12 | Matsushita Electric Ind Co Ltd | Scroll compressor |
JP2006266454A (en) * | 2005-03-25 | 2006-10-05 | Matsumura Koki Kk | Ring and sealing structure |
JP4035140B2 (en) * | 2005-07-22 | 2008-01-16 | 川崎重工業株式会社 | Turbine rotor seal ring |
US7465152B2 (en) * | 2005-09-16 | 2008-12-16 | General Electric Company | Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles |
US20070114727A1 (en) * | 2005-11-21 | 2007-05-24 | General Electric Company | Seal member, assembly and method |
DE602006006452D1 (en) * | 2006-09-25 | 2009-06-04 | Siemens Ag | Turbine rotor with closure plates and corresponding assembly process |
-
2009
- 2009-03-12 US US12/402,808 patent/US20100232939A1/en not_active Abandoned
-
2010
- 2010-03-03 EP EP10155312.1A patent/EP2236768A3/en not_active Withdrawn
- 2010-03-10 JP JP2010052474A patent/JP5475511B2/en not_active Expired - Fee Related
- 2010-03-12 CN CN2010101468881A patent/CN101893001A/en active Pending
Patent Citations (55)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3043562A (en) * | 1961-04-10 | 1962-07-10 | Gen Electric | Combination sealing and restraining member for long-shank turbo-machine buckets |
US3137478A (en) * | 1962-07-11 | 1964-06-16 | Gen Electric | Cover plate assembly for sealing spaces between turbine buckets |
US3501249A (en) * | 1968-06-24 | 1970-03-17 | Westinghouse Electric Corp | Side plates for turbine blades |
US3751183A (en) * | 1971-12-02 | 1973-08-07 | Gen Electric | Interblade baffle and damper |
US3768924A (en) * | 1971-12-06 | 1973-10-30 | Gen Electric | Boltless blade and seal retainer |
US3814539A (en) * | 1972-10-04 | 1974-06-04 | Gen Electric | Rotor sealing arrangement for an axial flow fluid turbine |
US3829233A (en) * | 1973-06-27 | 1974-08-13 | Westinghouse Electric Corp | Turbine diaphragm seal structure |
US3853425A (en) * | 1973-09-07 | 1974-12-10 | Westinghouse Electric Corp | Turbine rotor blade cooling and sealing system |
US4019833A (en) * | 1974-11-06 | 1977-04-26 | Rolls-Royce (1971) Limited | Means for retaining blades to a disc or like structure |
US4021138A (en) * | 1975-11-03 | 1977-05-03 | Westinghouse Electric Corporation | Rotor disk, blade, and seal plate assembly for cooled turbine rotor blades |
US4088421A (en) * | 1976-09-30 | 1978-05-09 | General Electric Company | Coverplate damping arrangement |
US4218189A (en) * | 1977-08-09 | 1980-08-19 | Rolls-Royce Limited | Sealing means for bladed rotor for a gas turbine engine |
US4265594A (en) * | 1978-03-02 | 1981-05-05 | Bbc Brown Boveri & Company Limited | Turbine blade having heat localization segments |
US4326835A (en) * | 1979-10-29 | 1982-04-27 | General Motors Corporation | Blade platform seal for ceramic/metal rotor assembly |
US4480958A (en) * | 1983-02-09 | 1984-11-06 | The United States Of America As Represented By The Secretary Of The Air Force | High pressure turbine rotor two-piece blade retainer |
US4507052A (en) * | 1983-03-31 | 1985-03-26 | General Motors Corporation | End seal for turbine blade bases |
US4523890A (en) * | 1983-10-19 | 1985-06-18 | General Motors Corporation | End seal for turbine blade base |
US4500098A (en) * | 1983-12-22 | 1985-02-19 | United Technologies Corporation | Gas seal for rotating components |
US4659285A (en) * | 1984-07-23 | 1987-04-21 | United Technologies Corporation | Turbine cover-seal assembly |
US4645424A (en) * | 1984-07-23 | 1987-02-24 | United Technologies Corporation | Rotating seal for gas turbine engine |
US4659289A (en) * | 1984-07-23 | 1987-04-21 | United Technologies Corporation | Turbine side plate assembly |
US4743164A (en) * | 1986-12-29 | 1988-05-10 | United Technologies Corporation | Interblade seal for turbomachine rotor |
US4781534A (en) * | 1987-02-27 | 1988-11-01 | Westinghouse Electric Corp. | Apparatus and method for reducing windage and leakage in steam turbine incorporating axial entry blade |
US5222742A (en) * | 1990-12-22 | 1993-06-29 | Rolls-Royce Plc | Seal arrangement |
US5236302A (en) * | 1991-10-30 | 1993-08-17 | General Electric Company | Turbine disk interstage seal system |
US5275534A (en) * | 1991-10-30 | 1994-01-04 | General Electric Company | Turbine disk forward seal assembly |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
US5257909A (en) * | 1992-08-17 | 1993-11-02 | General Electric Company | Dovetail sealing device for axial dovetail rotor blades |
US5338154A (en) * | 1993-03-17 | 1994-08-16 | General Electric Company | Turbine disk interstage seal axial retaining ring |
US5503528A (en) * | 1993-12-27 | 1996-04-02 | Solar Turbines Incorporated | Rim seal for turbine wheel |
US5429478A (en) * | 1994-03-31 | 1995-07-04 | United Technologies Corporation | Airfoil having a seal and an integral heat shield |
US6120249A (en) * | 1994-10-31 | 2000-09-19 | Siemens Westinghouse Power Corporation | Gas turbine blade platform cooling concept |
US5954477A (en) * | 1996-09-26 | 1999-09-21 | Rolls-Royce Plc | Seal plate |
US5803710A (en) * | 1996-12-24 | 1998-09-08 | United Technologies Corporation | Turbine engine rotor blade platform sealing and vibration damping device |
US6189891B1 (en) * | 1997-03-12 | 2001-02-20 | Mitsubishi Heavy Industries, Ltd. | Gas turbine seal apparatus |
US6086329A (en) * | 1997-03-12 | 2000-07-11 | Mitsubishi Heavy Industries, Ltd. | Seal plate for a gas turbine moving blade |
US5967745A (en) * | 1997-03-18 | 1999-10-19 | Mitsubishi Heavy Industries, Ltd. | Gas turbine shroud and platform seal system |
US6106234A (en) * | 1997-12-03 | 2000-08-22 | Rolls-Royce Plc | Rotary assembly |
US5993160A (en) * | 1997-12-11 | 1999-11-30 | Pratt & Whitney Canada Inc. | Cover plate for gas turbine rotor |
US6220814B1 (en) * | 1998-07-16 | 2001-04-24 | Siemens Westinghouse Power Corporation | Turbine interstage sealing arrangement |
US6273683B1 (en) * | 1999-02-05 | 2001-08-14 | Siemens Westinghouse Power Corporation | Turbine blade platform seal |
US6561764B1 (en) * | 1999-03-19 | 2003-05-13 | Siemens Aktiengesellschaft | Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms |
US6190131B1 (en) * | 1999-08-31 | 2001-02-20 | General Electric Co. | Non-integral balanced coverplate and coverplate centering slot for a turbine |
US6315298B1 (en) * | 1999-11-22 | 2001-11-13 | United Technologies Corporation | Turbine disk and blade assembly seal |
US6776573B2 (en) * | 2000-11-30 | 2004-08-17 | Snecma Moteurs | Bladed rotor disc side-plate and corresponding arrangement |
US6506016B1 (en) * | 2001-11-15 | 2003-01-14 | General Electric Company | Angel wing seals for blades of a gas turbine and methods for determining angel wing seal profiles |
US20060021218A1 (en) * | 2002-08-23 | 2006-02-02 | Mcmillan Alison J | Seals and a method of making seals |
US6945749B2 (en) * | 2003-09-12 | 2005-09-20 | Siemens Westinghouse Power Corporation | Turbine blade platform cooling system |
US7264447B2 (en) * | 2003-12-05 | 2007-09-04 | Honda Motor Co., Ltd. | Sealing arrangement for an axial turbine wheel |
US7241109B2 (en) * | 2004-06-04 | 2007-07-10 | Rolls-Royce Plc | Seal system |
US7121800B2 (en) * | 2004-09-13 | 2006-10-17 | United Technologies Corporation | Turbine blade nested seal damper assembly |
US7264448B2 (en) * | 2004-10-06 | 2007-09-04 | Siemens Power Corporation, Inc. | Remotely accessible locking system for turbine blades |
US7189055B2 (en) * | 2005-05-31 | 2007-03-13 | Pratt & Whitney Canada Corp. | Coverplate deflectors for redirecting a fluid flow |
US20070258816A1 (en) * | 2005-09-26 | 2007-11-08 | Pratt & Whitney Canada Corp. | Blades for a gas turbine engine with integrated sealing plate and method |
US20100196164A1 (en) * | 2009-02-05 | 2010-08-05 | General Electric Company | Turbine Coverplate Systems |
Cited By (12)
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US20100239413A1 (en) * | 2009-03-23 | 2010-09-23 | General Electric Company | Apparatus for turbine engine cooling air management |
US20100239414A1 (en) * | 2009-03-23 | 2010-09-23 | General Electric Company | Apparatus for turbine engine cooling air management |
US8142141B2 (en) * | 2009-03-23 | 2012-03-27 | General Electric Company | Apparatus for turbine engine cooling air management |
US8277172B2 (en) | 2009-03-23 | 2012-10-02 | General Electric Company | Apparatus for turbine engine cooling air management |
US8845284B2 (en) | 2010-07-02 | 2014-09-30 | General Electric Company | Apparatus and system for sealing a turbine rotor |
US20130094969A1 (en) * | 2011-10-17 | 2013-04-18 | General Electric Company | System for sealing a shaft |
US9217334B2 (en) | 2011-10-26 | 2015-12-22 | General Electric Company | Turbine cover plate assembly |
US8864453B2 (en) | 2012-01-20 | 2014-10-21 | General Electric Company | Near flow path seal for a turbomachine |
US9080456B2 (en) | 2012-01-20 | 2015-07-14 | General Electric Company | Near flow path seal with axially flexible arms |
US10337344B2 (en) * | 2014-05-27 | 2019-07-02 | Siemens Aktiengesellschaft | Turbomachine with an ingestion shield and use of the turbomachine |
US20170107837A1 (en) * | 2015-10-20 | 2017-04-20 | General Electric Company | Turbine slotted arcuate leaf seal |
US10161257B2 (en) * | 2015-10-20 | 2018-12-25 | General Electric Company | Turbine slotted arcuate leaf seal |
Also Published As
Publication number | Publication date |
---|---|
CN101893001A (en) | 2010-11-24 |
JP5475511B2 (en) | 2014-04-16 |
JP2010216657A (en) | 2010-09-30 |
EP2236768A2 (en) | 2010-10-06 |
EP2236768A3 (en) | 2014-12-24 |
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