CN103291376A - Rotating turbomachine component having a tip leakage flow guide - Google Patents
Rotating turbomachine component having a tip leakage flow guide Download PDFInfo
- Publication number
- CN103291376A CN103291376A CN2013100649436A CN201310064943A CN103291376A CN 103291376 A CN103291376 A CN 103291376A CN 2013100649436 A CN2013100649436 A CN 2013100649436A CN 201310064943 A CN201310064943 A CN 201310064943A CN 103291376 A CN103291376 A CN 103291376A
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- Prior art keywords
- stator parts
- stator
- turn
- parts
- angle
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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
- F01D5/12—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
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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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
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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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
Abstract
The invention relates to a rotating turbomachine component having a tip leakage flow guide. The rotating turbomachine component includes a base portion and an airfoil portion extending from the base portion. The airfoil portion includes a first end connected to the base portion and a tip end portion that is cantilevered from the base portion. A tip leakage flow guide is provided at the tip end portion of the airfoil portion. The tip leakage flow guide includes one or more turning vane members configured and disposed to guide a leakage flow from the tip end portion at a flow angle that substantially coincides with a flow angle of gases flowing downstream from the rotating turbomachine component.
Description
Technical field
Theme disclosed herein relates to the turbo machine field, and more particularly, relates to the rotary turbine mechanism part with terminal leakage flow guide.
Background technique
Many turbo machines comprise compressor section and the burner assembly that is linked in the turbine part by common compressor/turbine shaft or rotor.Compressor section is passed many continuous levels with pressurized air stream towards the burner assembly guiding.In burner assembly, pressurized air stream and fuel mix are to form ignition mixture.Ignition mixture burns to form hot gas in burner assembly.Hot gas is directed to the turbine part by transition piece.The rotary turbine blade that hot gas expander passes turbine to be producing merit, and this merit for example is output to drive generator, pump or provides power to vehicle.Except the pressurized air that is provided for burning, for the cooling purpose, the part of pressurized air stream is passed the turbine part.
In some cases, expand and pass the leakage of hot gasses of turbine part, perhaps on the end portion of turbine blade, pass through.In order to reduce leakage, MANUFACTURER keeps the end portion of turbo machine and the close clearance between the fixed component.Usually, Sealing is arranged on fixed component or the turbine shroud.Still allow the part of hot gas or gas leakage to pass through above the part endways though effectively, have Sealing now.The close clearance of being set up by Sealing makes gas leakage leave with the angle that is in substantially parallel relationship to the axis that is limited by turbine rotor.By contrast, the hot gas that transmits along gas path leaves rotor blade with angle.Interaction between gas leakage and the hot gas that flows along gas path produces local compression and descends, and it has negative influence to turbine performance.
Summary of the invention
According to an aspect of exemplary embodiment, a kind of rotary turbine mechanism part comprises base portion part and the airfoil section that partly extends from base portion.Airfoil section comprises base portion part and the end portion of partly giving prominence to from base portion.Terminal leakage flow guide is arranged on the terminal part office of airfoil section.Terminal leakage flow guide comprises one or more stator parts that turn to, its structure and be configured to with gas from the flow angle of rotary turbine mechanism part flow further downstream roughly consistent flow angle guide leakage flow from end portion.
Another aspect according to exemplary embodiment, a kind of method of operating turbine comprises: from burner assembly towards a plurality of movable vanes transmit hot gass, hot gas be directed on a plurality of movable vanes, with respect to a plurality of movable vanes along gas path with first flow that hot gas is guided in the angle downstream, the part that makes hot gas with the end portion of second flow angle at a plurality of movable vanes that is different from first flow angle above process, and with first jiao roughly consistent the 3rd flow angle guide the part of hot gas from the end portion of a plurality of movable vanes.
According to another aspect of exemplary embodiment, a kind of turbo machine comprises that compressor section, fluid ground connect the burner assembly of compressor section, and the turbine part that is connected in burner assembly with mechanically being linked in compressor section and fluid.The turbine portion branch comprises rotating member, the airfoil section that it has the base portion part and partly extends from base portion.Airfoil section comprises the first end that is connected in the base portion part and the end portion of partly giving prominence to from base portion.Terminal leakage flow guide is arranged on the terminal part office of airfoil section.Terminal leakage flow guide comprises one or more stator parts that turn to, its structure and be configured to with gas from the flow angle of rotary turbine mechanism part flow further downstream roughly consistent flow angle guide leakage flow from end portion.Turn to the stator support unit to be positioned at the terminal part office.Turn to the stator support unit to comprise end, upstream and downstream end.One or more stator parts that turn to outwards protrude from turning to the stator support unit.
The advantage of these and other and feature will become more apparent from the following description of carrying out by reference to the accompanying drawings.
Description of drawings
Being considered to theme of the present invention is pointed out and prescription clearly in the claim of ending place of specification especially.Of the present invention aforementioned and other feature and advantage from carry out by reference to the accompanying drawings following be specifically described as apparent, in this accompanying drawing:
Fig. 1 is the schematic representation of turbo machine according to comprising of exemplary embodiment of terminal leakage flow guide;
Fig. 2 is the partial section of the turbo machine of Fig. 1;
Fig. 3 is the detailed view of rotating member of turbo machine of Fig. 1 according to comprising of exemplary embodiment of terminal leakage flow guide;
Fig. 4 is the perspective view according to the terminal leakage flow guide of a plurality of Fig. 3 that turn to the stator parts of having of an aspect of exemplary embodiment;
Fig. 5 is the perspective view according to the terminal leakage flow guide of a plurality of Fig. 3 that turn to the stator parts of having of another aspect of exemplary embodiment; And
Fig. 6 is the perspective view according to the terminal leakage flow guide of a plurality of Fig. 3 that turn to the stator parts of having of another aspect of exemplary embodiment.
Detailed description is via example reference description of drawings embodiments of the invention and advantage and feature.
List of parts
2 turbo machines
4 compressor section
6 turbine parts
8 burner assemblies
The individual circumferentially burner at interval more than 10
12 compressors/turbine shaft
18 gas paths
19 housings
20 first order
21 second level
30 first order stator or nozzles
31 nozzle platforms
32 first order movable vane or blades
34 first order impeller of rotor
38 base portion parts
40 airfoil sections
42 first ends
44 the second ends or end portion
48 second level stator or nozzles
49 nozzle platforms
50 second level movable vane or blades
60 terminal leakage flow guides
64 stator support units
End, 66 upstream
68 downstream ends
The surface of 70 general planar
74 seal elements
80 stator parts
85 first-class or main flows
88 second stream or leakage flow
88 leakage flow
91 diverted flow
More than 97 substantial linear stator parts
99 first ends
100 the second ends
102 aerofoil profile
106 turn to stator
More than 110 crooked stator parts
112 first curved surfaces
113 second curved surfaces
117 turn to stator
121 complex geometry stator parts
123 first stator parts
124 second stator parts
126 first end sections
127 the second end sections
129 first ends
130 the second ends.
Embodiment
With reference to figure 1 and Fig. 2, represent with 2 substantially according to the turbo machine of exemplary embodiment structure.Turbo machine 2 comprises the compressor section 4 that functionally is connected in turbine part 6.Be connected in compressor section 4 and turbine part 6 burner assembly 8 fluids.Burner assembly 8 is formed by a plurality of circumferentially burners at interval, and one in the burner at these a plurality of circumferentially intervals with 10 expressions.Of course it is to be understood that burner assembly 8 can comprise other layout of burner.Compressor section 4 also is linked in turbine part 6 by common compressor/turbine shaft 12.Utilize this layout, compressor section 4 arrives burner assembly 8 with compressed air delivery.Pressurized air mixes with combustible fluid, to form ignition mixture.Ignition mixture burns in burner 10, to form the products of combustion that is transported to turbine part 6 by the transition piece (not shown).Products of combustion expands along the gas path 18 of turbine part 6, to provide power to for example (also not shown) such as generator, pump or vehicles.
In the exemplary embodiment that illustrates, turbine part 6 comprises that encirclement limits the first order 20 of gas path 18 and the housing 19 of the second level 21.The first order 20 comprises a plurality of first order stators or the nozzle that is supported on turbine shroud 19 by nozzle platform 31, and one in these a plurality of first order stators or the nozzle with 30 expressions.The first order 20 also comprises a plurality of first order movable vanes or the blade that is installed on first order impeller of rotor 34, and one in these a plurality of first order movable vanes or the blade with 32 expressions.Blade 32 and secure shroud parts 35 intervals.Blade 32 comprises base portion part 38 and airfoil section 40.Airfoil section 40 comprise the first end 42 that is connected in base portion part 38 and with secure shroud parts 35 the second end or end portion 44 at interval.The second level 21 comprises a plurality of second level stator or the nozzle that is supported on turbine shroud 19 by nozzle platform 49, and one in this a plurality of second level stator or the nozzle with 48 expressions.The second level 21 also comprises a plurality of second level movable vane or blade, and one in this a plurality of second level movable vane or the blade with 50 expressions.In this, should be appreciated that in the turbine part 6 the level quantity can change.
According to exemplary embodiment, turbo machine 2 comprises terminal leakage flow guide 60, and it is adjusted in the terminal leakage flow of process above the end portion of blade 32.As illustrating best in Fig. 3, what terminal leakage flow guide 60 comprised the end portion 44 that is installed on blade 32 turns to stator support unit 64.Turn to stator support unit 64 to comprise that the surface 70 by general planar extends to the end, upstream 66 of downstream end 68.Seal element 74 extends to the recess (not marking dividually) of secure shroud parts 35 from the surface 70 of general planar.Seal element 74 restriction is across the end portion 44 of blade 36 stream from gas path 18 processes.Yet though reduce, although there is seal element 74, some leakage flow still flow above the part 44 endways.In order to reduce the loss relevant with leakage flow, one or morely turn to stator parts 80 to be positioned to turn on the stator support unit 64.In the illustrative aspects that illustrates, turn to stator parts 80 to be arranged to contiguous downstream end 68.Turn to stator parts 80 to change the flow path of leakage flow.
Combustion gas flow along gas path 18, and on nozzle 30 process, and guided towards blade 32.First-class or main flow 85 process on blade 32, and second stream or leakage flow 88 are passed through part 44 above endways along gas path 18.Because with the interaction of blade 36, so main flow 85 is moving with the first mobile angular flux.Leakage flow 88 flows with second flow angle, and this second flow angle is different from first flow angle, and parallel substantially with axle 12.The leakage flow 88 that turns to stator parts 80 to be configured to regulate to leave end portion 44 or it is turned to, roughly consistent with first flow angle from the main flow 85 of blade 32 flow further downstream to produce diverted flow 91, the three flow angle that turn back to gas path 18 with the 3rd flow angle.By making the 3rd flow angle and first flow angle coupling, reduce the undesirable interaction between diverted flow 91 and the main flow 85.In this mode, turn to stator parts 80 reduce with caused by the undesirable interaction between leakage flow 88 and the main flow 85, along the interior loss of the relevant turbine part of the pressure variation of gas path 18 6.Form at nozzle 30 under the situation of a part of final stage (mark) dividually of turbine parts 6, turn to stator 80 can be configured to angle guiding leakage flow gas, recover in order to strengthen pressure, this angle is substantially corresponding to towards the radial diffusion section (not shown) of turbine part 6 and along the gas flow angle of its flow further downstream.
According to an aspect of the exemplary embodiment shown in Fig. 4, turn to stator parts 80 to take the form of a plurality of substantial linear stator parts 97.Each stator parts 97 comprises first end 99 and the second end 100.The second end 100 makes stator parts 97 angled with respect to for example axle 12 with respect to first end 99 biasings.More specifically, stator parts 97 are angled, so that cardinal principle is corresponding to the aerofoil profile 102 of airfoil section 40.According to an aspect of exemplary embodiment, the angle of stator parts 97 be substantially equal to the trailing edge angle θ of aerofoil profile 102 or aerofoil profile 102 trailing edge angle θ ± 30 °.Fig. 5 shows and turns to stator 106 according to another aspect of exemplary embodiment.Turn to stator 106 to take to have the form of a plurality of crooked stator parts 110 of first curved surface 112 and second curved surface 113.In the mode similar to mode described above, stator parts 110 are angled, so that cardinal principle is corresponding to the aerofoil profile 102 of airfoil section 40.According to an aspect of exemplary embodiment, the angle of stator parts 110 be substantially equal to the trailing edge angle θ of aerofoil profile 102 or aerofoil profile 102 trailing edge angle θ ± 30 °.Fig. 6 shows and turns to stator 117 according to another aspect of exemplary embodiment.Turn to stator 117 to take the form of complex geometry stator parts 121.Complex geometry stator parts 121 comprise the first stator parts 123 and the second stator parts 124.The first stator parts 123 comprise the first end section 126 that extends to the second end section 127.The second stator parts 124 comprise the first end 129 that extends to the second end 130 from the second end section 127 of the first stator parts 123.The second end 130 is with respect to first end section 126 biasings and angled of the first stator parts 123, so that cardinal principle is corresponding to the aerofoil profile 102 of airfoil section 40.According to an aspect of exemplary embodiment, the angle of the second end 130 be substantially equal to the trailing edge angle θ of aerofoil profile 102 or aerofoil profile 102 trailing edge angle θ ± 30 °.Form of tubes not, turn to stator with leakage flow be adjusted to with main flow roughly consistent angle be transmitted back in the gas path, to reduce undesirable interaction.
In this, should be appreciated that exemplary embodiment provides following system, it gets back to gas path for terminal leakage flow is guided again, with the undesirable interaction of minimizing with main flow.Reduce the minimizing that undesirable interaction with main flow causes reducing the pressure loss of turbine performance.Though it is also understood that together with combustion gas turbine to illustrate, exemplary embodiment also can be used in steam turbine.
Though only describe the present invention in detail together with the embodiment of limited quantity, should understand easily, the present invention is not subject to this disclosed embodiment.On the contrary, the present invention can be changed into incorporate into so far do not describe but match with the spirit and scope of the present invention, any amount of variation, change, replacement or equivalent arrangements.In addition, though described various embodiment of the present invention, will understand, aspect of the present invention can only comprise some among the embodiment of description.Therefore, the present invention is not counted as by aforementioned description and limits, but is only limited by the scope of claims.
Claims (20)
1. rotary turbine mechanism part, it comprises:
The base portion part;
Airfoil section, it partly extends from described base portion, and described airfoil section comprises the first end that is connected in described base portion part and the end portion of partly giving prominence to from described base portion; And
Terminal leakage flow guide, it is arranged on the terminal part office of described airfoil section, described terminal leakage flow guide comprises one or more stator parts that turn to, its structure and be configured to with gas from the flow angle of described rotary turbine mechanism part flow further downstream roughly consistent flow angle from described end portion guiding leakage flow.
2. rotary turbine according to claim 1 mechanism part, it is characterized in that, also comprise: what be positioned at described terminal part office turns to the stator support unit, the described stator support unit that turns to has end, upstream and downstream end, in end, described upstream and the described downstream end each is protruded and is surpassed described end portion, and described one or more stator parts that turn to outwards protrude from the described stator support unit that turns to.
3. rotary turbine according to claim 2 mechanism part is characterized in that described terminal leakage flow guide is arranged in the described downstream end place that turns to the stator support unit.
4. rotary turbine according to claim 1 mechanism part, it is characterized in that, described one or more stator parts that turn to comprise a plurality of substantial linear stator parts that extend across described end portion, in described a plurality of substantial linear stator parts each comprises first end and the second end, and described the second end is setovered with respect to described first end.
5. rotary turbine according to claim 1 mechanism part is characterized in that, described one or more stator parts that turn to comprise a plurality of crooked stator parts that extend across described end portion.
6. rotary turbine according to claim 1 mechanism part is characterized in that, described one or more stator parts that turn to comprise a plurality of complex geometry stator parts that extend across described end portion.
7. rotary turbine according to claim 6 mechanism part, it is characterized in that, in described a plurality of complex geometry stator parts each comprises the first stator parts and the second stator parts, the described first stator parts have the first end section that extends to the second end section, the described second stator parts have the first end that extends to the second end from the second end section of the described first stator parts, and described the second end is setovered with respect to described first end section.
8. rotary turbine according to claim 1 mechanism part is characterized in that, described one or more stator parts that turn to are arranged with the angle corresponding to the aerofoil profile of described airfoil section substantially.
9. the method for an operating turbine, it comprises:
Transmit hot gas from burner assembly towards a plurality of movable vanes;
Described hot gas is directed on described a plurality of movable vane;
Guide described hot gas along gas path with the first mobile angle downstream with respect to described a plurality of movable vanes;
The part of described hot gas is passed through on the end portion of described a plurality of movable vanes with second flow angle that is different from described first flow angle; And
With with described first flow angle roughly consistent the 3rd flow angle guide the part of described hot gas from the end portion of described a plurality of movable vanes.
10. method according to claim 9 is characterized in that, a part that transmits described hot gas from described end portion comprises across one or more parts that turn to the stator parts to guide described hot gas that are arranged in described terminal part office.
11. method according to claim 10 is characterized in that, comprises that across one or more parts that turn to the stator parts to guide described hot gas a part that makes described hot gas passes through on a plurality of angled stator parts.
12. method according to claim 10 is characterized in that, comprises that across one or more parts that turn to the stator parts to guide described hot gas a part that makes described hot gas passes through on a plurality of crooked stator parts.
13. method according to claim 10, it is characterized in that, across one or more parts that turn to the stator parts to guide described hot gas comprise with described a plurality of movable vanes in each airfoil section angle substantially corresponding angle transmit the part of described hot gas.
14. a turbo machine, it comprises:
Compressor section;
Burner assembly, its fluid ground connects described compressor section;
The turbine part, it is connected in described burner assembly with mechanically being linked in described compressor section and fluid, described turbine portion branch comprises rotating member, the airfoil section that it has the base portion part and partly extends from described base portion, described airfoil section comprise the first end that is connected in described base portion part and the end portion of partly giving prominence to from described base portion;
Terminal leakage flow guide, it is arranged on the terminal part office of described airfoil section, described terminal leakage flow guide comprises one or more stator parts that turn to, its structure and be configured to with gas from the flow angle of described rotating member flow further downstream roughly consistent flow angle from described end portion guiding leakage flow; And
Turn to the stator support unit, it is positioned at described terminal part office, and the described stator support unit that turns to has end, upstream and downstream end, and described one or more stator parts that turn to outwards protrude from the described stator support unit that turns to.
15. turbo machine according to claim 14 is characterized in that, described one or more stator parts that turn to are arranged corresponding to the angle of the aerofoil profile of described airfoil section with cardinal principle.
16. turbo machine according to claim 15 is characterized in that, described one or more angles that turn to the stator parts are not more than in about 30 ° the trailing edge angle of described aerofoil profile.
17. turbo machine according to claim 14, it is characterized in that, described one or more stator parts that turn to comprise a plurality of substantial linear stator parts that extend across described end portion, in described a plurality of substantial linear stator parts each comprises first end and the second end, and described the second end is setovered with respect to described first end.
18. turbo machine according to claim 13 is characterized in that, described one or more stator parts that turn to comprise a plurality of crooked stator parts that extend across described end portion.
19. turbo machine according to claim 13 is characterized in that, described one or more stator parts that turn to comprise a plurality of complex geometry stator parts that extend across described end portion.
20. turbo machine according to claim 19, it is characterized in that, described a plurality of complex geometry stator parts comprise the first stator parts and the second stator parts, the described first stator parts have the first end section that extends to the second end section, the described second stator parts have the first end that extends to the second end from the second end section of the described first stator parts, and described the second end is setovered with respect to described first end section.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/409,637 US20130230379A1 (en) | 2012-03-01 | 2012-03-01 | Rotating turbomachine component having a tip leakage flow guide |
| US13/409,637 | 2012-03-01 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103291376A true CN103291376A (en) | 2013-09-11 |
Family
ID=48142266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013100649436A Pending CN103291376A (en) | 2012-03-01 | 2013-03-01 | Rotating turbomachine component having a tip leakage flow guide |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20130230379A1 (en) |
| JP (1) | JP2013181543A (en) |
| CN (1) | CN103291376A (en) |
| DE (1) | DE102013101902A1 (en) |
| GB (1) | GB2501169A (en) |
| RU (1) | RU2013108927A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454026A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Zigzag-shroud of aero-engine rotor vane |
| CN104847416A (en) * | 2015-04-09 | 2015-08-19 | 上海理工大学 | Impeller top surrounding band and turbine |
| CN104929699A (en) * | 2015-06-05 | 2015-09-23 | 赵军 | Novel supercharged sealing labyrinth |
| CN108119189A (en) * | 2016-11-30 | 2018-06-05 | 通用电气公司 | Blade, rotating machinery and its assemble method |
| CN114320487A (en) * | 2022-01-07 | 2022-04-12 | 中国航发贵阳发动机设计研究所 | Grate tooth sealing structure and method suitable for same |
| CN114450466A (en) * | 2019-09-26 | 2022-05-06 | 川崎重工业株式会社 | Turbine blade |
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| JP5591042B2 (en) * | 2010-09-17 | 2014-09-17 | 三菱重工業株式会社 | Turbine |
| US9777582B2 (en) | 2012-07-03 | 2017-10-03 | United Technologies Corporation | Tip leakage flow directionality control |
| US9957817B2 (en) | 2012-07-03 | 2018-05-01 | United Technologies Corporation | Tip leakage flow directionality control |
| US9951629B2 (en) | 2012-07-03 | 2018-04-24 | United Technologies Corporation | Tip leakage flow directionality control |
| JP5985351B2 (en) * | 2012-10-25 | 2016-09-06 | 三菱日立パワーシステムズ株式会社 | Axial flow turbine |
| US10247025B2 (en) * | 2013-04-03 | 2019-04-02 | Mitsubishi Heavy Industries, Ltd. | Rotating machine |
| JP2015094220A (en) * | 2013-11-08 | 2015-05-18 | 三菱日立パワーシステムズ株式会社 | Axial flow turbine |
| MX2017012325A (en) | 2015-04-08 | 2017-12-20 | Horton Inc | Fan blade surface features. |
| EP3147460A1 (en) * | 2015-09-23 | 2017-03-29 | General Electric Technology GmbH | Axial flow turbine |
| GB201519869D0 (en) * | 2015-11-11 | 2015-12-23 | Rolls Royce Plc | Shrouded turbine blade |
| WO2017200549A1 (en) * | 2016-05-20 | 2017-11-23 | Siemens Aktiengesellschaft | Tip shroud with a fence feature for discouraging pitch-wise over-tip leakage flow |
| JP6986426B2 (en) * | 2017-11-29 | 2021-12-22 | 三菱重工業株式会社 | Turbine |
| FR3125085A1 (en) * | 2021-07-12 | 2023-01-13 | Safran Aircraft Engines | Turbomachine blade |
| CN115324657A (en) * | 2022-10-12 | 2022-11-11 | 中国航发四川燃气涡轮研究院 | Turbine working blade shroud cooling structure |
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2012
- 2012-03-01 US US13/409,637 patent/US20130230379A1/en not_active Abandoned
-
2013
- 2013-02-26 DE DE102013101902A patent/DE102013101902A1/en not_active Withdrawn
- 2013-02-28 JP JP2013039309A patent/JP2013181543A/en active Pending
- 2013-02-28 RU RU2013108927/06A patent/RU2013108927A/en not_active Application Discontinuation
- 2013-03-01 GB GB1303700.7A patent/GB2501169A/en not_active Withdrawn
- 2013-03-01 CN CN2013100649436A patent/CN103291376A/en active Pending
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454026A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Zigzag-shroud of aero-engine rotor vane |
| CN104847416A (en) * | 2015-04-09 | 2015-08-19 | 上海理工大学 | Impeller top surrounding band and turbine |
| CN104929699A (en) * | 2015-06-05 | 2015-09-23 | 赵军 | Novel supercharged sealing labyrinth |
| CN104929699B (en) * | 2015-06-05 | 2016-05-11 | 中国民用航空飞行学院 | A kind of booster-type comb tooth of obturaging |
| CN108119189A (en) * | 2016-11-30 | 2018-06-05 | 通用电气公司 | Blade, rotating machinery and its assemble method |
| CN108119189B (en) * | 2016-11-30 | 2022-05-17 | 通用电气公司 | Blade, rotary machine, and method of assembling same |
| CN114450466A (en) * | 2019-09-26 | 2022-05-06 | 川崎重工业株式会社 | Turbine blade |
| CN114450466B (en) * | 2019-09-26 | 2023-08-29 | 川崎重工业株式会社 | turbine blade |
| CN114320487A (en) * | 2022-01-07 | 2022-04-12 | 中国航发贵阳发动机设计研究所 | Grate tooth sealing structure and method suitable for same |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102013101902A1 (en) | 2013-09-05 |
| GB2501169A (en) | 2013-10-16 |
| RU2013108927A (en) | 2014-09-10 |
| US20130230379A1 (en) | 2013-09-05 |
| GB201303700D0 (en) | 2013-04-17 |
| JP2013181543A (en) | 2013-09-12 |
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Effective date of abandoning: 20171117 |