CN111734497A - Turbine rotor blade and gas turbine comprising same - Google Patents
Turbine rotor blade and gas turbine comprising same Download PDFInfo
- Publication number
- CN111734497A CN111734497A CN202010734232.5A CN202010734232A CN111734497A CN 111734497 A CN111734497 A CN 111734497A CN 202010734232 A CN202010734232 A CN 202010734232A CN 111734497 A CN111734497 A CN 111734497A
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- Prior art keywords
- blade
- turbine rotor
- cold air
- rotor blade
- platform
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Links
- 238000001816 cooling Methods 0.000 claims abstract description 65
- 238000007789 sealing Methods 0.000 claims abstract description 48
- 230000003334 potential effect Effects 0.000 claims abstract description 23
- 238000003754 machining Methods 0.000 claims description 10
- 238000005266 casting Methods 0.000 claims description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims description 2
- 238000009826 distribution Methods 0.000 abstract description 7
- 230000008646 thermal stress Effects 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 15
- 230000000694 effects Effects 0.000 description 5
- 239000013589 supplement Substances 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000009545 invasion Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- 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
- F01D5/187—Convection cooling
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A turbine rotor blade and a gas turbine comprising the same are provided, wherein the turbine rotor blade comprises a cold air hole which is arranged on a blade platform, and one end of the cold air hole is communicated to a potential effect influence area corresponding to the upper surface of the blade platform; and/or the cold air hole is arranged on the blade root of the blade, and one end of the cold air hole is communicated to the corresponding wheel rim sealing area below the blade platform; the other end of the cooling air hole is communicated to the interior of the turbine rotor blade and is used for introducing cooling air in the interior of the turbine rotor blade. The invention can more accurately control the flow of the cooling air in the blade platform area under the condition of not increasing the total cooling air amount, so that the distribution of the cooling air in the circumferential direction is more reasonable and controllable, and the temperature and the thermal stress level of the blade platform area are reduced.
Description
Technical Field
The invention relates to the technical field of turbine rotor cooling, in particular to a turbine rotor blade and a gas turbine comprising the same.
Background
With the increasing level of gas turbine design technology, the gas turbine inlet gas temperature is increasing continuously, and the thermal load of turbine parts is extremely high, and the limit that high-temperature materials can bear is already exceeded. In order to ensure safe and reliable operation of the turbine blade, it is necessary to design the turbine blade with a complex cooling system to maintain the temperature and stress distribution of the blade body at a reasonable level.
In the cooling design process of the turbine rotor blade, the pressure fluctuation in the platform region of the blade is severe, the distribution of the cold air amount in the platform region is often uneven along the circumferential direction, so that the cooling effect is often poor, and therefore the platform region of the turbine rotor blade is very easy to cause the phenomena of high temperature or high-temperature oxidation due to overlarge thermal stress, cracking, even ablation and the like due to uneven distribution of the cooling air.
Therefore, there is a need for more precise control of the flow of cooling air in the platform region of the blade without increasing the total cooling air volume, so that the distribution thereof in the circumferential direction is more rational and controllable, in order to reduce the temperature and thermal stress level in the platform region of the blade.
Disclosure of Invention
In view of the above, it is a primary object of the present invention to provide a turbine rotor blade and a gas turbine including the same, which are intended to at least partially solve at least one of the above-mentioned technical problems.
In order to achieve the purpose, the technical scheme of the invention is as follows:
as one aspect of the present invention, a turbine rotor blade is provided, comprising a blade body, a blade root, and a blade platform connecting the blade body and the blade root; the outer surface of the blade body of the blade comprises a suction surface and a pressure surface, and the junction areas of the suction surface and the pressure surface are the front edge and the tail edge of the blade respectively; a rim sealing area is arranged below the blade platform, and a potential effect influence area is arranged at the upstream of the front edge of the blade;
the turbine rotor blade further includes:
the cold air hole is arranged on the blade platform, and one end of the cold air hole is communicated to the potential effect influence area corresponding to the upper surface of the blade platform; and/or
The cold air holes are arranged on the blade roots of the blades, and one ends of the cold air holes are communicated to the corresponding wheel rim sealing areas below the blade platforms;
the other end of the cold air hole is communicated to the interior of the turbine rotor blade and is used for introducing cooling air in the interior of the turbine rotor blade.
As another aspect of the present invention, there is also provided a gas turbine including the turbine rotor blade as described above.
Based on the technical scheme, compared with the prior art, the invention has at least one or one part of the following beneficial effects:
the blade platform is provided with a rim seal for injecting sealing air in a rim seal area above the blade platform, and the area close to the blade platform is cooled and protected by the sealing air; the influence of the potential effect influence area can cause that the sealing air is not evenly distributed along the circumferential direction; the invention designs the cold air hole, and the cold air of the cold air hole can come from the cooling channel in the blade or from the sealing space at the root of the blade. Under the condition of not increasing the total cooling air quantity, the cooling design quality of the blade platform area can be obviously improved, so that the potential effect of the front edge of the rotor blade on the upstream flow is weakened, the cooling effect of the area is improved, and the gas is effectively prevented from invading the sealing area of the wheel rim;
the cold air holes are formed in the blade platform and below the blade platform at the same time, so that the cooling effect is better.
Drawings
FIG. 1 is a schematic representation of a turbine rotor blade meridian plane cross section in accordance with an embodiment of the present invention;
FIG. 2 is a perspective view of a turbine rotor blade according to an embodiment of the present invention;
FIG. 3 is a potential diagram according to an embodiment of the present invention;
FIG. 4 is a schematic illustration of the sealing air flow rate in the rim seal area under the influence of potential effects of an embodiment of the present invention.
In the above figures, the reference numerals have the following meanings:
10-moving blade protective ring; 11-blade root; 12-a blade platform; 13-blade body; 14-a cooling channel; 15-blade root seal space; 16-platform upper cold air holes; 17-platform lower cold air holes; an 18-potential effect affected zone; 20-body mean camber line; 31-suction surface; 32-pressure side; 33-blade leading edge; 34-the trailing edge of the blade; 35-a rim seal area; 36-rim sealing; 40-stationary blades; 41-a vane upper endwall; 42-a vane lower endwall; a-high temperature fuel gas; b-sealing air; c-cooling air; d, gas invasion; e-concentration of cold air.
Detailed Description
The turbine rotor blade of the gas turbine provided by the invention can control the flow of cooling air in the blade platform area more accurately under the condition of not increasing the total cooling air amount, so that the distribution of the cooling air in the circumferential direction is more reasonable and controllable, and the temperature and the thermal stress level of the blade platform area are reduced.
In order that the objects, technical solutions and advantages of the present invention will become more apparent, the present invention will be further described in detail with reference to the accompanying drawings in conjunction with the following specific embodiments.
As one aspect of the present invention, a turbine rotor blade is provided, the turbine rotor blade comprising a blade body, a blade root, and a blade platform connecting the blade body and the blade root; the outer surface of the blade body of the blade comprises a suction surface and a pressure surface, and the junction areas of the suction surface and the pressure surface are the front edge and the tail edge of the blade respectively; a rim sealing area is arranged below the blade platform, and a potential effect influence area is arranged at the upstream of the front edge of the blade;
the turbine rotor blade further includes:
the cold air hole is arranged on the blade platform, and one end of the cold air hole is communicated to the potential effect influence area corresponding to the upper surface of the blade platform; and/or
One end of the cold air hole is communicated to the corresponding wheel rim sealing area below the blade platform;
the other end of the cooling air hole is communicated to the interior of the turbine rotor blade and is used for introducing cooling air in the interior of the turbine rotor blade.
In an embodiment of the invention, the other end of the cooling air hole is connected to a sealed space inside the blade root or a cooling channel inside the turbine rotor blade.
In embodiments of the present invention, the cold air holes are in a circular, oval, rectangular or slit configuration.
In an embodiment of the present invention, the cold gas hole forming method includes machining, electro-machining, or casting.
In the embodiment of the invention, the turbine rotor blade is a solid blade, and the other end of the cold air hole is communicated to the sealing space inside the blade root; the sealing space in the blade root is a cavity formed by assembling adjacent blades and the sealing device.
In the embodiment of the invention, the turbine rotor blade is a hollow blade, the other end of the cold air hole is communicated to a cooling channel inside the turbine rotor blade, and the cooling channel is formed by casting or machining.
In an embodiment of the present invention, the cold air holes include a plurality of first cold air holes and a plurality of second cold air holes; the turbine rotor blade is a hollow blade;
the first cold air hole is arranged on the blade platform, and one end of the first cold air hole is communicated to the potential effect influence area corresponding to the upper surface of the blade platform; the other end of the first cold air hole is communicated to a cooling channel inside the turbine rotor blade, and the cooling channel is formed by casting or machining;
the second cold air hole is arranged on the blade root of the blade, and one end of the second cold air hole is communicated to the corresponding wheel rim sealing area below the blade platform; the other end of the second cold air hole is communicated to a sealing space inside a blade root of the turbine rotor blade; the sealing space in the blade root is a cavity formed by assembling adjacent blades and the sealing device.
In the embodiment of the invention, the first cold air hole and the second cold air hole are respectively arranged in plurality along the circumferential direction of the front edge of the blade and used for reducing the fluctuation of the air pressure of the potential effect influence area.
In an embodiment of the invention, a rim seal is provided on the blade platform for injecting sealing air in the region of the rim seal above the blade platform.
As another aspect of the present invention, there is also provided a gas turbine including the turbine rotor blade as described above.
The technical solution of the present invention is further described below with reference to specific examples, but it should be noted that the following examples are only for illustrating the technical solution of the present invention, but the present invention is not limited thereto.
FIG. 1 provides a schematic representation of a turbine rotor blade meridian plane cross-section of an embodiment of the present invention. The high-temperature combustion gas a is accelerated and turned by the stationary blade 40, and then enters a space formed by the blade platform 12 of the rotor blade and the blade shroud ring 10 along a space formed by the stationary blade upper endwall 41 and the stationary blade lower endwall 42, and then strikes the blade body 13 to perform work.
The manner of cooling blade platform 12 is illustrated in FIG. 1. Sealing air B in the rotor blade rim sealing area 35 seals the lower area of the blade platform 12 through the rim seal 36, so that high-temperature gas is prevented from invading; meanwhile, the sealing air B forms an air film to cover the upper part of the blade platform 12, so that the platform is cooled and protected, and high-temperature failure of the platform is prevented.
Due to the potential effect of the downstream rotor blade leading edge, as shown in FIG. 3, the pressure distribution fluctuates and a potential effect region 18 resembling a triangle (or a sinusoidal curve) is created upstream of the rotor blades, which increases in pressure. As shown in fig. 4, the sealing air ejected through the rim seal 36 in the rotor blade rim sealing area 35 is no longer uniformly distributed along the circumferential direction, the sealing air flow in the potential effect influence area 18 is significantly reduced, and even gas backflow occurs, which seriously jeopardizes the safety of the gas turbine.
FIG. 2 is a perspective view of a turbine rotor blade according to an embodiment of the present invention. From the blade root 11, the cooling air C enters the rotor blade internal cooling channels 14 and the blade root seal 15. When the sealing air is unevenly distributed at the rim sealing area 35 due to the potential effect of the leading edge 33 of the rotor blade, at least one platform upper cooling air hole 16 is arranged in the potential effect influence area 18 of the upper surface of the blade platform 12 for introducing cooling air of the blade internal cooling channel 14; the cold air holes can be in a round, oval, rectangular, gap and other structures, and can be formed by machining, electromachining and casting; a lower rim sealing region 35 of the bucket platform 12, arranged with at least one lower platform cooling air hole 17 for introducing cooling air to the bucket interior cooling passage 14; the cold air holes can be round, oval, rectangular, gap and the like, and can be formed by machining, electromachining and casting.
In other embodiments of the invention, cooling air C enters the rotor blade interior cooling channels 14 and the blade root seal 15 from the blade root 11. When the sealing air is unevenly distributed in the rim sealing area 35 due to the potential effect of the leading edge 33 of the rotor blade, at least one platform upper cold air hole 16 is arranged in the potential effect influence area 18 on the upper surface of the blade platform 12 and used for introducing the cooling air of the blade root sealing space 15, the cold air hole can be in a circular, oval, rectangular, gap and other structures, and can be formed by machining, electromachining and casting; the lower rim sealing area 35 of the blade platform 12 is provided with at least one platform lower cooling air hole 17 for introducing cooling air into the blade root sealing space 15, the cooling air hole may be circular, oval, rectangular, slit, etc., and the cooling air hole may be machined, electro-machined, cast or gap-formed.
Similar to the two embodiments above, the cooling air for the platform upper cooling air holes 16 may come from the cooling passages 14, and the cooling air for the platform lower cooling air holes 17 from the blade root seal 15; alternatively, the cooling air for the lower platform cooling apertures 17 may be from the cooling passages 14 and the cooling air for the upper platform cooling apertures 16 may be from the blade root enclosure 15.
The cold air holes 17 at the lower part of the platform supplement the sealing air, so that the sealing air flow in the potential effect influence area 18 in the wheel rim sealing area 35 is effectively improved, and the potential effect influence generated by the blade body 13 of the downstream blade is effectively reduced; the cold air holes 16 on the upper part of the platform supplement the sealing air, the cold air covering and convection heat exchange effects of the potential effect influence area 18 on the upper part of the movable vane platform 12 are effectively improved, and the heat exchange and temperature level of the area can be effectively reduced.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A turbine rotor blade, comprising a blade body, a blade root, and a blade platform connecting the blade body and the blade root; the outer surface of the blade body of the blade comprises a suction surface and a pressure surface, and the junction areas of the suction surface and the pressure surface are the front edge and the tail edge of the blade respectively; a rim sealing area is arranged below the blade platform, and a potential effect influence area is arranged at the upstream of the front edge of the blade;
the turbine rotor blade further includes:
the cold air hole is arranged on the blade platform, and one end of the cold air hole is communicated to the potential effect influence area corresponding to the upper surface of the blade platform; and/or
The cold air holes are arranged on the blade roots of the blades, and one ends of the cold air holes are communicated to the corresponding wheel rim sealing areas below the blade platforms;
the other end of the cold air hole is communicated to the interior of the turbine rotor blade and is used for introducing cooling air in the interior of the turbine rotor blade.
2. The turbine rotor blade according to claim 1, wherein the other end of the cold air hole communicates with a sealed space inside the blade root or a cooling channel inside the turbine rotor blade.
3. The turbine rotor blade according to claim 1, wherein the cold air holes are of a circular, elliptical, rectangular or slotted configuration.
4. The turbine rotor blade according to claim 1, wherein the cold gas hole is formed by a method comprising machining, electro-machining, or casting.
5. The turbine rotor blade according to claim 1 wherein said turbine rotor blade is a solid blade and the other end of said cold air hole communicates with a sealed space inside the blade root; and the sealing space in the blade root is a cavity formed by assembling adjacent blades and sealing devices.
6. The turbine rotor blade according to claim 1 wherein the turbine rotor blade is a hollow blade and the other end of the cooling air hole communicates with a cooling channel inside the turbine rotor blade, the cooling channel being cast or machined.
7. The turbine rotor blade according to claim 1, wherein the cold air holes comprise a first plurality of cold air holes and a second plurality of cold air holes; the turbine rotor blade is a hollow blade;
the first cold air hole is arranged on the blade platform, and one end of the first cold air hole is communicated to the potential effect influence area corresponding to the upper surface of the blade platform; the other end of the first cold air hole is communicated to a cooling channel inside the turbine rotor blade, and the cooling channel is formed by casting or machining;
the second cold air hole is arranged on the blade root of the blade, and one end of the second cold air hole is communicated to the corresponding wheel rim sealing area below the blade platform; the other end of the second cold air hole is communicated to a sealing space inside a blade root of the turbine rotor blade; the sealing space in the blade root is a cavity formed by assembling adjacent blades and the sealing device.
8. The turbine rotor blade according to claim 7, wherein the first and second cooling holes are respectively provided in plural numbers along a circumferential direction of the leading edge of the blade for reducing fluctuations in air pressure in the potential-affected zone.
9. The turbine rotor blade according to claim 1, wherein a rim seal is provided on the blade platform for injecting sealing air in the region of the rim seal above the blade platform.
10. A gas turbine comprising a turbine rotor blade according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010734232.5A CN111734497A (en) | 2020-07-27 | 2020-07-27 | Turbine rotor blade and gas turbine comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010734232.5A CN111734497A (en) | 2020-07-27 | 2020-07-27 | Turbine rotor blade and gas turbine comprising same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111734497A true CN111734497A (en) | 2020-10-02 |
Family
ID=72656223
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010734232.5A Pending CN111734497A (en) | 2020-07-27 | 2020-07-27 | Turbine rotor blade and gas turbine comprising same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111734497A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5340278A (en) * | 1992-11-24 | 1994-08-23 | United Technologies Corporation | Rotor blade with integral platform and a fillet cooling passage |
| US5382135A (en) * | 1992-11-24 | 1995-01-17 | United Technologies Corporation | Rotor blade with cooled integral platform |
| US6341939B1 (en) * | 2000-07-31 | 2002-01-29 | General Electric Company | Tandem cooling turbine blade |
| EP1207268A1 (en) * | 2000-11-16 | 2002-05-22 | Siemens Aktiengesellschaft | Gas turbine blade and a process for manufacturing a gas turbine blade |
| JP2010059966A (en) * | 2008-09-04 | 2010-03-18 | General Electric Co <Ge> | Turbine bucket for turbomachine and method of reducing bow wave effect at the turbine bucket |
| CN102454427A (en) * | 2010-10-29 | 2012-05-16 | 通用电气公司 | Apparatus, systems and methods for cooling the platform region of turbine rotor blades |
| US20130202408A1 (en) * | 2012-02-07 | 2013-08-08 | Vincent P. Laurello | Gas turbine engine with improved cooling between turbine rotor disk elements |
| US20170370230A1 (en) * | 2015-01-09 | 2017-12-28 | Siemens Aktiengesellschaft | Blade platform cooling in a gas turbine |
| CN212535769U (en) * | 2020-07-27 | 2021-02-12 | 北京全四维动力科技有限公司 | Turbine rotor blade and gas turbine comprising same |
-
2020
- 2020-07-27 CN CN202010734232.5A patent/CN111734497A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5340278A (en) * | 1992-11-24 | 1994-08-23 | United Technologies Corporation | Rotor blade with integral platform and a fillet cooling passage |
| US5382135A (en) * | 1992-11-24 | 1995-01-17 | United Technologies Corporation | Rotor blade with cooled integral platform |
| US6341939B1 (en) * | 2000-07-31 | 2002-01-29 | General Electric Company | Tandem cooling turbine blade |
| EP1207268A1 (en) * | 2000-11-16 | 2002-05-22 | Siemens Aktiengesellschaft | Gas turbine blade and a process for manufacturing a gas turbine blade |
| JP2010059966A (en) * | 2008-09-04 | 2010-03-18 | General Electric Co <Ge> | Turbine bucket for turbomachine and method of reducing bow wave effect at the turbine bucket |
| CN102454427A (en) * | 2010-10-29 | 2012-05-16 | 通用电气公司 | Apparatus, systems and methods for cooling the platform region of turbine rotor blades |
| US20130202408A1 (en) * | 2012-02-07 | 2013-08-08 | Vincent P. Laurello | Gas turbine engine with improved cooling between turbine rotor disk elements |
| US20170370230A1 (en) * | 2015-01-09 | 2017-12-28 | Siemens Aktiengesellschaft | Blade platform cooling in a gas turbine |
| CN212535769U (en) * | 2020-07-27 | 2021-02-12 | 北京全四维动力科技有限公司 | Turbine rotor blade and gas turbine comprising same |
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