CN110005476A - Lapping sealing device - Google Patents
Lapping sealing device Download PDFInfo
- Publication number
- CN110005476A CN110005476A CN201811531048.XA CN201811531048A CN110005476A CN 110005476 A CN110005476 A CN 110005476A CN 201811531048 A CN201811531048 A CN 201811531048A CN 110005476 A CN110005476 A CN 110005476A
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- CN
- China
- Prior art keywords
- blade
- slot
- lapping
- adjacent
- sealing element
- 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
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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
- 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
-
- 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
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The lapping device of gas turbine with axis；Comprising: which the first and second blades, are disposed adjacently along the circumferential direction centered on axis；Each blade radially includes stabilizer blade, the handle portions equipped with downstream closure wall, platform and the airfoil for being configured to for blade being connected to rotor；Cooling air cavity is set in handle portions between adjacent blades, is sealed in outside by the axial seal of the gap arrangement between adjacent platforms, is sealed in downstream by the lapping connector between adjacent shank closure wall；Lapping connector includes corresponding receiving recess portions in the circumferential protrusion and adjacent shank closure wall of the shank closure wall of the first blade；Radial seal, gap arrangement between its protrusion and recess portions along lapping connector, it is contained at side in the first radial slot realized in protrusion, it is contained at the other side in the second radial slot realized in recess portions, to provide defence across the barrier of the leakage stream of lapping connector.
Description
Cross-reference to related applications
This application claims the priority of the European patent application No. 17207850.3 submitted on December 15th, 2017, the Europe
The disclosure of patent application is merged by reference.
Technical field
Lapping (shiplap) device that the present invention relates to a kind of for gas turbine.
Background technique
For the conventional hermetic means of sealed spacer, such as rubber seal, polymer seal, bonding device, or make
Protruding portion is bonded in slot (as encountered in the case where the sealing especially between two static cells), is generally
Know.In gas turbine, Various Components are cooled down by means of cooling air stream perhaps, to avoid thermal damage.The cooling air stream
It should be embodied as that there is loss as minimum as possible, to maximize cooling potential.
It is efficiently sealed between two blade elements in gas turbine to realize, such as in order to prevent due to leakage stream
Caused by cooling air loss, make blade element each other accurately matching be necessary.However, if it is desired to make adjacent structure
Part may have a certain " gap ", and (such as between two rotor blades in the rotor of gas turbine, " gap " is essential
, this is because the high current as caused by thermodynamic medium around blade element during operation), then the two of blade element
The accurate matching of a adjacent shield is nearly impossible, because the construction of such compact is (as radial clearance
To be necessary for being fully sealed like that) it can lead to problem (for example, due to thermal expansion).Also, after mounting, component it
Between the influence of centrifugal force can be quite big, this can lead to being seriously worn for conventional hermetic device.For those reasons, so-called
" lapping part " is used according between the blade in the reaction wheel of conventional design, for sealing leakage in axial direction
Stream." lapping part " constitutes heat-resisting air locking because they substantially by the design of material of blade element itself, form blade
Therefore the composition part of the one of element, and realizes sealing effect, without may be to thermo-responsive or with different thermal expansions
The additional material of coefficient.
In most cases, turbo blade radially has at least one platform in inside and/or radially outward
Element, in the case where blade arranges mounted situation, two be directed toward along circumferential direction side that platform element passes through platform element
It abuts against on the correspondingly adjacent platform element of correspondingly adjacent blade element, to be respectively formed in every case substantially
For circumferential gap.In at least one axial edge (especially back edge), such turbo blade element is in circumferentially side
To on the first side of direction, can have prominent in the platform element for extending and being projected into adjacent blade element along circumferential direction
Portion out, and on the second side being directed toward along circumferential direction, there can be the recess portion for accommodating the protruding portion.
The sequence installation of such blade element causes to be formed between two blade elements in every case so-called
" lapping part ".Such lapping part is that the sheath elements in the axial edge of blade element are identical as adjacent blade element
Axial edge on sheath elements between overlapping or engaging zones, along the flow direction of working gas be it is stepped.
The lapping part seals the gap that radially extends between the circumferential sides of two turbo blades adjoined, with guard against cooling air from
The evolution of auxiliary air circuit, that is, guard against leakage stream in axial direction.This lapping part due to by means of blade element along week
The protruding portion on the second side that is directed toward to direction covers the first side being directed toward along circumferential direction of adjacent blade element
On recess portion and formed, or by protruding portion be bonded in recess portion formed.
Summary of the invention
Therefore, the present invention is based on providing a kind of target of improved device, the improved device along lapping connector and
With improved sealing effect, which reduces the leakage stream from cooling air cavity.
The target is realized by lapping device according to claim 1.Device claimed ensures that lapping couples
Gap in part can be sealed.
Further object of the invention is to provide a kind of device, and in the apparatus, sealing element is rigid, and has
It is mounted in the case where gap in two opposite slots along lapping connector.It reduce production cost and ensure it is easy
Assembly.
Further object of the invention is to provide a kind of device, and in the apparatus, sealing element is hook-type, limits inverse
The concave side of leakage stream and the protruding portion in one slot in the convex side be directed toward and engagement, leakage stream make sealing element against protruding portion.
Which ensure that the suitable and easy positioning of sealing element and fixing.
Further object of the invention is to provide a kind of device, and in the apparatus, slot and sealing element are located in along taking
Between two bending sections in the gap of folded connector.Bending section is conventionally positioned in the stepped rear region of platform, and corresponding
Circumferential protruding portion in the platform for extending to adjacent leaf segments of platform.Bending section reduces the rate of leakage stream, and
The positioning of sealing element further reduced the rate of leakage stream.
Front describes the present invention referring to the lapping device sealed.However, the invention further relates to include such sealing
Lapping device blade row, and relate generally to it is a kind of equipped with such blade row the gas turbine for power plant.
It is to be understood that the description generally of front and detailed description below are both illustrative, and it is intended to
Further explaination such as claimed invention is provided.According to following description, drawings and claims, of the invention is other
Advantages and features will be apparent.
Specifically elaborate that of the invention is considered as novel feature in the dependent claims.
Detailed description of the invention
Suitably referring to attached drawing come after reading over detailed description, further benefit of the invention and advantage will
It becomes apparent.
However, by referring to detailed description below of the invention can be best understood the present invention itself, it is of the invention with
Under detailed description describe exemplary embodiment obtained from combination attached drawing of the invention, in the accompanying drawings:
Fig. 1 is the schematic diagram of the flow chart of the embodiment of the gas turbine for power plant；
Fig. 2 and Fig. 3 is the schematic diagram of two adjacent turbo blades of the gas turbine of Fig. 1；
Fig. 4 is the schematic diagram of the part of Fig. 3；
Fig. 5 is the schematic enlarged view for the part of Fig. 4 indicated by label V, with sealing device according to the present invention
Embodiment；
Fig. 6 and Fig. 7 is respectively the sealing device axially of Fig. 5 under the status of criterion of tolerance and under worst case
Schematic diagram；
Fig. 8 and Fig. 9 is the schematic diagram of the sealing device along radial direction of Fig. 5, and wherein sealing element is arranged in blade
In adjacent blade.
Specific embodiment
In conjunction with attached drawing, this is hereinafter described according to preferred embodiment (be not used in and limit execution range of the invention)
The technology contents and detailed description of invention.Any equivalent variations according to made by the appended claims and modification are by the present invention
Claimed claims are covered.
The present invention is described in detail now with reference to attached drawing.
It referring to Fig.1, is the schematic diagram of the flow chart of the embodiment of the gas turbine for power plant.Fig. 1 discloses combustion
Air turbine power plant 1 continuously includes: with axis A, and along mainstream M
Compressor section 2 is equipped with the entrance 11 for supplying air 10,
Combustor section is equipped with burner 3 and combustion chamber 4, and burner 3 has multiple fuel nozzles 6, in combustion chamber 4, pressure
Contracting air is mixed at least one fuel, and the mixture is ignited to form hot gas stream, and
Turbine 5, hot gas stream expands wherein, to do work to rotor 7.
Preferably, rotor 7 is the single part being made of the multiple rotor wheels welded together, and is extended to from compressor 2
Turbine 5.As it is known, combustor section can be equipped with annular burner or multiple tubular burners.Leave the exhaust gas of turbine
It can be used in steam generator 8, and rotor 7 may be connected to load 9, load 9 can be the power generation in fixed load, such as power plant
Machine.As it is known, compressor 2 and turbine 5 include multiple stator vanes and multiple rotating vanes.The connection of these rotating vanes
To rotor 7, and it is arranged to the parallel circumferential row centered on axis 7.
Referring to Fig. 2 and Fig. 3, Fig. 2 and Fig. 3 be Fig. 1 gas turbine adjacent blade schematic diagram, specifically, Fig. 2 and
Fig. 3 refers to adjacent turbo blade 12.As it is known, turbo blade is contacted with hot gas, and therefore need by cooling down
Air (i.e. compressed air) is cooling.Specifically, Fig. 2 discloses the legend of the Main way of field of gas turbines.In the legend,
Label 13 refers to axial direction, is parallel to rotor 7, axis A and is substantially parallel to hot gas stream direction M.Term downstream
With upstream referring to the axial direction 13 along hot gas stream direction M.Label 14 refers to the radial direction centered on axis A；
Inside term/it is inside and outside/outer non-economic along radial direction 14 distance away from axis A.Label 15 refer to
Circumferential direction centered on axis A.For clarity, Fig. 3-9 below also discloses the legend, to allow to readily recognize institute
The correct position of the gas turbine components of expression.In view of above, Fig. 2 discloses two adjacent turbines in same row's blade
The axial downstream view of blade 12.Blade 12 can be by metal, metal alloy, ceramic matrix composite (CMC) or other suitable materials
Material is constituted.Since axis A and along radial direction 14, each blade 12 includes the stabilizer blade 16 for being configured to couple with rotor 7, is equipped with
The handle portions 17 of downstream wall or closure wall 18, platform 19 and airfoil 20.Between two adjacent blades, in handle portions 17
Place is partly disclosed there are cavity, in particular cooling air cavity with label 21 in figs. 8 and 9.Cooling air can
From the cooling pipe that handle cavity enters that the inside in airfoil 20 is realized, airfoil 20 connects with hot gas stream in operation
Touching.The cavity is limited along radial direction 14 by the adjacent edge of platform 19 in outside, and in downstream axially 13
It is limited by the neighboring edge of closure wall 18.As it is known, the cooling is empty in order to avoid the loss of efficiency of turbogenerator
Air cavity both must have been sealed radially (that is, to avoid the leakage for passing to the gap being present between adjacent platform 19
Object), and in axial direction seal (that is, to avoid the leakage for passing to the gap being present between closure wall 18).Radially side
To sealing executed by axial seal, which is arranged in platform 19 preferably in the form of axial sealing stripe
Opposite neighboring edge axial seat in.Fig. 2 and Fig. 3 schematically discloses the axial seal with label 22, and Fig. 8 and
Fig. 9 discloses the seat 23 in platform 19 of the axial seal 22.Sealing in axial direction is by figure 2 and figure 3 by marking
Numbers 24 so-called lapping connectors indicated execute.As it is known, lapping connector 24 includes the protrusion of closure wall 19
That realizes to the radial edges of adjacent closure wall 19 and in such adjacent closure wall 19 is configured to for accommodating protrusion
The recess portion at edge.In order to assemble blade row, each blade (in addition to the blade at end) in row includes closure wall, in closure wall,
First radial edges 15 are equipped with protrusion along the circumferential direction, and adjacent equipped with being adapted to accommodate in opposite radial edges
Blade protrusion radial recess.
Fig. 3 schematically shows the top view along radial direction 14 of some adjacent blades, to illustrate lapping
Connector.Airfoil 20 includes leading edge 25 and back edge 26.Fig. 3 discloses close by axial direction between two adjacent platforms 19
The radial clearance 27 and be configured to the lapping for closing the axial gap between two adjacent closure walls 19 that sealing 22 seals
Connector 24.The protruding portion part of lapping connector 24 is indicated by label 28, and corresponding recess portion is indicated with label 29.
It is the schematic enlarged view of the laps of Fig. 3 referring to Fig. 4.Specifically, Fig. 4, which is disclosed, is arranged in front
Sealing element 30 in the lap regions 24 of description.The sealing element 30, which is configured to provide defence and passes through from handle cavity, is present in protrusion
The barrier of the leakage stream in the gap between portion part 28 and recess portions 29.
It is the schematic enlarged view of the part of Fig. 4 referring to Fig. 5, which is indicated by label V and shown to be equipped with sealing
The top view along radial direction of the lap regions 24 of part 30.
According to the embodiment of Fig. 5, the first slot 31 that sealing element 30 is realized from protruding portion part 28 is extended axially into
The second slot 32 realized in recess 29.Label C1 and C2 expression in Fig. 5 is passed through between two adjacent closure walls
The cooling air stream of (specifically, across the gap being present in protruding portion part 28 and recess portions 29).C1 is along axis
To the leakage stream in direction, and C2 is leakage stream along the circumferential direction.As disclosed in Fig. 5, sealing element 30 allows to hinder
Fluid stopping C2.Preferably, sealing element 30 is close in the rigidity being contained in slot 31 and slot 32 with clearance or in the case where gap
Sealing.First slot 31 and the second slot 32 are substantially along axial direction 13 and toward each other.
Referring now to Fig. 6 and Fig. 7, they are respectively the sealing device of Fig. 5 under the status of criterion of tolerance and worst case
Under schematic diagram.
Clearance of the sealing element 30 in relevant slot 21 and slot 32 ensures to make up manufacturing tolerance and obtains simultaneously appropriate close
Envelope.Specifically, gap edge is parallel to the direction of (i.e. along the circumferential direction 15) leakage stream C2, and/or transverse to (preferably,
Perpendicular to) direction of leakage stream C2 (i.e. axially 13).This makes 30 floating ground of rigid seal installation present 31,32
In.Moreover, sealing element 30 has the shape of hook, one slot 32 in the convex side 33 being directed toward against leakage stream C2 and engagement is limited
The concave side 34 of protruding portion 35 in (specifically, the slot 32 in recess portions 29).Since sealing element is present the sky of 31,32 inside
Gap, therefore coupling for Floating connection between sealing element 30 and protruding portion 35.In use, leakage stream C2 make sealing element 30 against
Protruding portion 35, even if centrifugal force acts on sealing element 30.
According to disclosed embodiment, sealing element 30 has the cross section of substantially " L " that is orthogonal to radial direction 14,
It is limited by the shorter arm 37 in the longer arm 36 across the gap of lapping connector and the slot 32 being contained in recess portions 29.L
Shape is easily fabricated (such as passing through bending).However, it is possible to using can manufacture (such as passing through extruding) other profiles (such as
" T " profile) obtain similar function.In use, leakage stream makes slot 31 of the longer arm 36 in recess portions 28
Interior surface, even if centrifugal force acts on sealing element 30.
Referring to Fig. 8 and Fig. 9, they are the perspective schematic view of the sealing device axially of Fig. 5, are shown respectively
It is arranged in the sealing element in blade and in adjacent blade.Specifically, Fig. 8 and Fig. 9 is disclosed respectively from handle cavity, from shank
Two axial perspective figures of the sealing element 30 that the outside of cavity obtains.According to this embodiment, sealing element 30 and slot 31,32 be substantially
It is radially extended along the entire radical length of protruding portion 28 and recess portion 29.
Sealing element 30 extends outwardly until arranging the axial seal in present 23 between adjacent blade.
Finally, the inner end of slot be it is open, to allow to be slidably assembled sealing element 30, sealing element 30 is in the opposite outer of slot
It is held in place at end.Preferably, sealing element 30 is kept by axial seal 22, assembles axial seal after assembling sealing element 30
Part 22.
Although illustrating the present invention about the preferred embodiment of the present invention as mentioned above, it is to be understood that,
In the case where without departing from the scope of the present invention, many other possible modifications and variations can be made.Therefore it is contemplated that appended power
Benefit requires or claims will cover these modifications and variations fallen within the true scope of the present invention.
Claims (12)
1. lapping device of the one kind for the gas turbine (1) with axis (A)；The lapping device (24) includes:
First blade and the second blade (12) are adjacent along the circumferential direction (15) centered on gas turbine axis (A)
Ground arrangement；Each blade (12) is along radial direction (14) and including being configured to for the blade (12) to be connected to rotor (7)
Stabilizer blade (16), be equipped with downstream closure wall (18) handle portions (17), platform (19) and airfoil (20)；In adjacent blade
(12) between, cooling air cavity (21) are set in the handle portions (17), the cooling air cavity (21) is in outside
It is sealed by the axial seal (22) arranged along the gap between adjacent platform (19), and in downstream by adjacent handle
Lapping connector (24) between portion's closure wall (18) seals；The lapping connector (24) includes first blade (12)
The circumferential protrusion (28) of the shank closure wall (18) and corresponding in adjacent shank closure wall (18) connect
It receives recess portions (29)；
Radial seal (30), along the protrusion (28) and the recess portions of the lapping connector (24)
(29) gap between and arrange, and the first radial slot realized in the protrusion (28) is contained at side
(31) it in, and is contained at the other side in the second radial slot (32) realized in the recess portions (29), it is anti-to provide
The barrier of the standby leakage stream across the lapping connector.
2. the apparatus according to claim 1, which is characterized in that the sealing element (30) is rigid, and with gap
In the case where be contained in the slot (31,32) so that the sealing element (30) floating ground is mounted on the slot (31,32)
In.
3. the apparatus of claim 2, which is characterized in that gap is along circumferential direction and/or in axial direction.
4. device according to any one of the preceding claims, which is characterized in that the sealing element (30) is hook-type,
It limits one in the convex side (33) being directed toward against the leakage stream and engagement first slot (31) and the second slot (32)
The concave side (34) of interior protruding portion (35), the leakage stream make the sealing element (30) against the protruding portion (35).
5. device according to claim 6, which is characterized in that the sealing element (30) includes across the lapping connector
(24) longer arm (36) in the gap between the protrusion (28) and the recess portions (29) and from it is described compared with
Long-armed (36) are prominent and are contained in the shorter arm (37) in second slot (32), the leakage together with the protruding portion (35)
Stream makes the longer arm (36) against the interior surface of first slot (31).
6. device according to any one of the preceding claims, which is characterized in that the slot (31,32) and described close
Sealing (30) is located between the protrusion (28) and the recess portions (29) along the lapping connector (24)
The gap two bending sections between.
7. device according to any one of the preceding claims, which is characterized in that the inner end of the slot (31,32) is
Open, to allow to be slidably assembled the sealing element (30).
8. device according to any one of the preceding claims, which is characterized in that the sealing element (30) is in the slot
(31,32) it is held in place at outer end.
9. device according to any one of the preceding claims, which is characterized in that the sealing element (30) passes through described
Axial seal (22) and be held in place, assemble the axial seal (22) after assembling the sealing element (30).
10. one kind arranges component for the blade of the gas turbine with axis (A), the blade row component includes:
First blade and the second blade (12) are adjacent along the circumferential direction (15) centered on gas turbine axis (A)
Ground arrangement；Each blade (12) is along radial direction (14) and including being configured to for the blade (12) to be connected to rotor (7)
Stabilizer blade (16), be equipped with downstream closure wall (18) handle portions (17), platform (19) and airfoil (20)；In adjacent blade
(12) between, cooling air cavity (21) are set in the handle portions (17), the cooling air cavity (21) is in outside
It is sealed by the axial seal (22) arranged along the gap between adjacent platform (19), and in downstream by adjacent handle
Lapping connector (24) between portion's closure wall (18) seals；The lapping connector (24) includes first blade (12)
The circumferential protrusion (28) of the shank closure wall (18) and corresponding in adjacent shank closure wall (18) connect
It receives recess portions (29)；
Radial seal (30), along the protrusion (28) and the recess portions of the lapping connector (24)
(29) gap between and arrange, and the first radial slot realized in the protrusion (28) is contained at side
(31) it in, and is contained at the other side in the second radial slot (32) realized in the recess portions (29), it is anti-to provide
The barrier of the standby leakage stream across the lapping connector.
11. blade according to claim 10 arranges component, which is characterized in that the sealing element (30) and the slot (31,
32) it is constructed as described in any one of preceding claims 1-9.
12. a kind of gas turbine for power plant；The gas turbine (1) has axis (A), and includes:
Compressor (2), is used for compressed air,
Burner (3,4), the compressed air for being used to make to leave the compressor (2) are mixed and are burnt at least one fuel,
Turbine (3), is used to make to leave the hot gas stream expansion through burning of the burner (3,4), and does to rotor (7)
Function；
Wherein, the turbine (3) includes at least one blade row component as described in claim 10 or 11.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP17207850.3 | 2017-12-15 | ||
| EP17207850.3A EP3498980B1 (en) | 2017-12-15 | 2017-12-15 | Shiplap seal arrangement |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110005476A true CN110005476A (en) | 2019-07-12 |
| CN110005476B CN110005476B (en) | 2022-11-08 |
Family
ID=60673741
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811531048.XA Active CN110005476B (en) | 2017-12-15 | 2018-12-14 | Overlapping sealing device |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP3498980B1 (en) |
| CN (1) | CN110005476B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1221539B1 (en) * | 2001-01-09 | 2006-04-19 | Mitsubishi Heavy Industries, Ltd. | Sealing for shrouds of a gas turbine |
| CN102373961A (en) * | 2010-08-20 | 2012-03-14 | 通用电气公司 | Turbine bucket assembly and method for assembling the same |
| CN104169545A (en) * | 2012-03-28 | 2014-11-26 | 三菱重工业株式会社 | Seal member, turbine, and gas turbine |
| CN104343472A (en) * | 2013-07-31 | 2015-02-11 | 阿尔斯通技术有限公司 | Turbine blade and turbine with improved sealing |
| CN104420891A (en) * | 2013-08-29 | 2015-03-18 | 阿尔斯通技术有限公司 | Blade of a rotary flow machine with a radial strip seal |
| US20170241283A1 (en) * | 2016-02-18 | 2017-08-24 | United Technologies Corporation | Stator vane shiplap seal assembly |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1995413B1 (en) * | 2007-04-05 | 2010-04-28 | ALSTOM Technology Ltd | Gap seal for airfoils of a turbomachine |
| ES2548441T3 (en) * | 2007-04-05 | 2015-10-16 | Alstom Technology Ltd | Beam overlap joint arrangement |
-
2017
- 2017-12-15 EP EP17207850.3A patent/EP3498980B1/en active Active
-
2018
- 2018-12-14 CN CN201811531048.XA patent/CN110005476B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1221539B1 (en) * | 2001-01-09 | 2006-04-19 | Mitsubishi Heavy Industries, Ltd. | Sealing for shrouds of a gas turbine |
| CN102373961A (en) * | 2010-08-20 | 2012-03-14 | 通用电气公司 | Turbine bucket assembly and method for assembling the same |
| CN104169545A (en) * | 2012-03-28 | 2014-11-26 | 三菱重工业株式会社 | Seal member, turbine, and gas turbine |
| CN104343472A (en) * | 2013-07-31 | 2015-02-11 | 阿尔斯通技术有限公司 | Turbine blade and turbine with improved sealing |
| CN104420891A (en) * | 2013-08-29 | 2015-03-18 | 阿尔斯通技术有限公司 | Blade of a rotary flow machine with a radial strip seal |
| US20170241283A1 (en) * | 2016-02-18 | 2017-08-24 | United Technologies Corporation | Stator vane shiplap seal assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110005476B (en) | 2022-11-08 |
| EP3498980A1 (en) | 2019-06-19 |
| EP3498980B1 (en) | 2021-02-17 |
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