CN100390377C - 制造涡轮叶片的方法 - Google Patents
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
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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
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
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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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
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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
- F05D2240/80—Platforms for stationary or moving blades
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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
- F05D2250/00—Geometry
- F05D2250/70—Shape
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/4998—Combined manufacture including applying or shaping of fluent material
- Y10T29/49988—Metal casting
- Y10T29/49989—Followed by cutting or removing material
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Abstract
在用于制造涡轮叶片的方法中,呈涡轮叶片基本形状的铸件(10’)在铸模中制造,为了完成涡轮叶片,铸件(10’)然后被进行去除材料的机加工。在这种类型的方法中,为了优化涡轮性能,通过改变铸件(10’)的机加工而保持同一铸模获得改变的前缘角,能够以简单快捷的方式改变叶片前缘角的几何形状。
Description
技术领域
本发明涉及涡轮领域。本发明涉及一种制造涡轮叶片的方法。
背景技术
当研制涡轮机级时,预先计算好的输出功率有时难以符合效率目标。由于产生大量偏差并导致一定差异,在涡轮叶片的铸造和机加工过程中会产生这些难点。在成品机器中,就研发和制造而言,在基准点计算和涡轮之间实际上也有差异。依靠差异量,需要进行随后的修正。因此,为了实际上能够获得涡轮的预先计算好的流动动力目标值,需要降低所述差异。
解决问题的一个基本方法是,以通过绕着纵轴线把涡轮叶片的轮廓旋转到需要的位置从而调整涡轮机级中气体流动路径的可能性为基础。
做到这一点的一个方法是使用可调整的铸模。例如,EP-A2-1216770披露了一种从用于涡轮叶片生产的蜡来浇铸成型件的工具和方法,其中,几个刀架被以预定方式正结合装配,形成将要被铸造的成型件的空腔。至少多个刀架中的一个接收可旋转或可移位的刀片或插入物,该刀片或插入物的一面与空腔接壤并能够相对于刀架被安装进不同的位置或方向。
已知的铸造工具容许不断改变成型件的几何形状,特别是其装置角或前缘几何形状,而不必为了这一目的生产新的刀架。然而,这种铸造工具的缺点是在铸造过程中的所有这些改变需要消耗大量的工作量和时间。
发明内容
因此,本发明的一个目的是提供一种用于生产涡轮叶片的方法,其避免了已经指出的已知的缺点,并为了优化涡轮性能,容许叶片前缘几何形状以特别简单快速的方式改变。
本发明目的能够通过如下技术方案来实现,即本发明提出了一种用于生产涡轮叶片的方法,在所述方法中,呈涡轮叶片基本形状的铸件在铸模中制造,然后,为了完成涡轮叶片,对铸件进行去除材料的机加工,其中,通过在保持同一铸模时改变铸件的机加工,获得被改变以优化涡轮的涡轮叶片前缘角,为了进行所述去除材料的机加工,附加机加工原料被设置在铸件上,附加机加工原料的厚度被选择成充分大于最小值2毫米,大于最小值的附加机加工原料总计可达5毫米,涡轮叶片具有在围绕叶片或者涡轮叶片的纵向轴线±3°的预定角度范围内自由选择的前缘角。
本发明的本质是通过改变铸件的机加工而保留相同的铸模来获得涡轮叶片的前缘角,所述前缘角已经被改变以优化涡轮。这种解决方法考虑了发现在叶片的研制已经结束之后,改变一般应该被完全避免或者尽可能早的完成,但同时,在生产程序中发生的这种类型的改变越靠后,它们就越成功。在机加工步骤中的任何改变仅仅影响机加工工具。与在铸造过程中进行的改变相比,这较大地降低了时间延迟。为了进行机加工,所述涡轮叶片的前缘角通过使铸件绕叶片纵轴线旋转通过一个修正角而改变。
本发明的第一个优选结构的特征在于,铸件在机加工过程中被夹持在夹具中,所述铸件在夹具中被旋转,以改变机加工,使机加工所需的基准点被重新定位。
作为选择,铸件可以与夹具一起旋转以变换机加工,使正确计算的距离被用于到达所需的位置。
本发明的一个尤其优选的结构特征在于,为了进行去除材料的机加工,附加机加工原料(machining stock)被设置在铸件上,附加机加工原料的厚度被选择成充分大于一最小值,使得具有在预定角度范围内自由选择的前缘角的涡轮叶片可通过机加工同一铸件而制成。
这样,如果铸件或涡轮叶片具有叶片平台和主叶片部件,并且如果大于最小值的附加机加工原料被设置在叶片平台上,将会特别方便。
对于附加机加工原料来说,其最小值优选为大约2毫米,对于大于最小值的附加机加工原料来说总计可达5毫米。
附图说明
本发明的更完全的理解和其中伴随的优点将更被易于获得,同样通过参考连同附图考虑时的下面的详细描述变得更加易于理解。
图1示出现有的用于具有叶片平台和主叶片部件的涡轮叶片的铸件的俯视平面图,具有设置在叶片平台上的2毫米的附加机加工原料;
图2以类似于图1的方式示出本发明第一个示例的实施例,在叶片平台上铸件具有高出最小值2毫米的附加机加工原料,因此,甚至可能从同一铸件生产涡轮叶片,所述涡轮叶片已经能够在顺时针方向旋转3°;和
图3以类似于图1的方式示出本发明第二个示例的实施例,在叶片平台上,铸件具有高出最小值2毫米的附加机加工原料,因此,对于涡轮叶片来说,甚至能够从同一铸件生产,所述涡轮叶片已经在逆时针方向旋转3°。
具体实施方式
现参照附图,其中,在几个附图中,相同的附图标记指的是同一或对应的部件,图1所示的是根据现有技术,第一级涡轮叶片的铸件示例从上方所看到的俯视图,该涡轮叶片具有叶片平台和主叶片部件。铸件10具有(例如)外部尺寸为124.6毫米×133.8毫米的矩形叶片平台11。实际的主叶片部件12相对于叶片平台11的位置决定了随后产生的涡轮叶片的前缘角(也比较在引言中引用的EP-A2-1216770的图2),主叶片部件12沿着纵轴13从叶片平台11向上延伸。以其本身公知的方式,在叶片平台11的外边缘周围(在图1虚线所示的矩形和实线所示的矩形之间的区域)提供2毫米的附加机加工原料14。这种附加机加工原料14提供用于铸件10随后的去除材料机加工的材料,所述铸件给出了涡轮叶片的最终形状。
现在本发明的中心思想在于以这种方式设计铸件的外部尺寸,即在随后的机加工过程中,能够在一定的角度范围内自由地选择前缘角,因此前缘角能够通过机加工操作与涡轮的特定状态匹配,而不必改变铸模。为了这一目的,对需要在叶片的相应表面上进行机加工的附加机加工原料来说,为了尽可能的与旋转的叶片一起进行机加工,需要将其增加到超出最小值足够多。所述角度可得到的范围越大,必须选择的附加机加工原料的厚度越厚。附加机加工原料的增加的厚度必须考虑到铸件的蜡模,并稍微增加了机加工费用。
图2和3示出了附加机加工原料增加的厚度的两个示例:这样设计图2所示的铸件10’,即能够通过在顺时针方向(图2所示的旋转箭头方向)转动3°改变随后产生的涡轮叶片的前缘角。图3所示的铸件10″被这样设计,即能够通过在逆时针方向(图3所示的旋转箭头方向)转动3°改变随后产生的涡轮叶片的前缘角。
在图2和图3中,开始位置(没有附加旋转)在叶片平台11的区域被以虚线示出。旋转3°的结果是以虚线形式被示出的矩形转化为以实线示出的两个矩形中较小的一个。主叶片部件12也随之相应地旋转。如果旋转的主叶片部件12以不旋转的叶片平台11(以虚线示出)为基础,所述平台与前缘角的转动一致,叶片平台11的外边界必须按照实线所示的两个矩形的外边,被向外移动到足够远,以便相对虚线所示的矩形保留2毫米的最小距离来作为附加机加工原料,所述虚线所示的矩形代表在机加工后获得的叶片平台。那么铸件10’的叶片平台11的外部尺寸为131.1mm×140mm(附加机加工原料14’;图2),铸件10″的叶片平台的外部尺寸为131.2mm×140mm(附加机加工原料14″;图3)。如果使用的开始点是实线所示的两个矩形中较大的一个,可以通过从铸件10’或10″去除材料远至虚线所示的矩形对已经被旋转-3°或+3°的涡轮叶片进行机加工。
为了进行机加工,铸件10’或10″能够以两种方式被置于机加工具的夹具中:在一种情况中,铸件在夹具中旋转,使需要机加工的基准点被重新定位。在另一种情况中,铸件与夹具一起旋转,在这种情况下,正确计算的距离被用于到达所需的位置。
根据本发明,在铸造之后,旋转的涡轮叶片的选择主要用于调整第一级的导流叶片,以便为了获得改善涡轮的目的。
在这种情况下,叶片被旋转最大+/-2°。与大约2毫米的标准机加工材料相比较,这就需要大约5毫米的附加机加工材料。在这种情况下,优选用于机加工的是铸件与夹具一起旋转。
明显地,根据上面的教导,本发明可以有多种变化和改变。因此,易于理解,在本发明要求保护的范围内,本发明也可以所述方式之外的方式实施。
附图标记表
10,10’,10″铸件
11 叶片平台
12 主叶片部件
13 纵轴
14,14’,14″附加机加工原料
Claims (4)
1.一种用于生产涡轮叶片的方法,在所述方法中,呈涡轮叶片基本形状的铸件(10,10’,10″)在铸模中制造,然后,为了完成涡轮叶片,对铸件(10,10’,10″)进行去除材料的机加工,其中,通过在保持同一铸模时改变铸件(10,10’,10″)的机加工,获得被改变以优化涡轮的涡轮叶片前缘角,为了进行所述去除材料的机加工,附加机加工原料(14,14’,14”)被设置在铸件(10,10’,10″)上,附加机加工原料(14,14’,14″)的厚度被选择成充分大于最小值2毫米,大于最小值的附加机加工原料(14’,14″)总计可达5毫米,涡轮叶片具有在围绕涡轮叶片的纵向轴线±3°的预定角度范围内自由选择的前缘角。
2.如权利要求1所述的方法,其特征在于,在机加工过程中,铸件(10,10’,10″)被保持在夹具中,铸件(10,10’,10″)在夹具中被旋转以改变机加工,使机加工所需的基准点被重新定位。
3.如权利要求1所述的方法,其特征在于,在机加工过程中,铸件(10,10’,10″)被保持在夹具中,铸件(10,10’,10″)和夹具一起旋转以改变机加工。
4.如权利要求1所述的方法,其特征在于,铸件(10,10’,10″)或者涡轮叶片具有叶片平台(11)和主叶片部件(12),大于最小值的附加机加工原料(14’,14″)被设置在叶片平台(11)上。
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DE10255346A DE10255346A1 (de) | 2002-11-28 | 2002-11-28 | Verfahren zum Herstellen einer Turbinenschaufel |
DE10255346.7 | 2002-11-28 |
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EP (1) | EP1424466A3 (zh) |
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DE102004062174A1 (de) * | 2004-12-17 | 2006-06-22 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zur Herstellung von hoch belastbaren Bauteilen durch Präzisionsschmieden |
FR2890878B1 (fr) * | 2005-09-22 | 2009-04-24 | Snecma Sa | Procede de fabrication d'aubes de turbomachines par fonderie a la cire perdue. |
US20120159785A1 (en) * | 2009-09-04 | 2012-06-28 | BayerMaerialScience LLC | Automated processes for the production of polyurethane wind turbine blades |
BR112012013064A2 (pt) * | 2009-11-30 | 2017-05-23 | Snecma | processo de realização de um reforço metálico de bordo de ataque ou bordo de fuga de pá de turbomáquina |
CN102649219A (zh) * | 2011-02-25 | 2012-08-29 | 温永林 | 一种仿形活刀架加工工艺 |
CN102962653A (zh) * | 2012-11-09 | 2013-03-13 | 哈尔滨汽轮机厂有限责任公司 | 汽轮机次末级动叶片三轴数控加工方法 |
US8720526B1 (en) * | 2012-11-13 | 2014-05-13 | Siemens Energy, Inc. | Process for forming a long gas turbine engine blade having a main wall with a thin portion near a tip |
CN102962654B (zh) * | 2012-11-22 | 2015-01-21 | 哈尔滨汽轮机厂有限责任公司 | 一种汽轮机无冠部导叶片的加工方法 |
US9561555B2 (en) | 2012-12-28 | 2017-02-07 | United Technologies Corporation | Non-line of sight electro discharge machined part |
FR3050778B1 (fr) * | 2016-04-27 | 2020-02-14 | Safran Aircraft Engines | Pompe a jet pour turbomachine, comprenant un aubage pour mise en rotation de fluide actif |
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GB627295A (en) * | 1946-04-10 | 1949-08-05 | Adrian Albert Lombard | Improvements in or relating to the manufacture of guide vanes for axial-flow turbines and compressors |
US5299353A (en) * | 1991-05-13 | 1994-04-05 | Asea Brown Boveri Ltd. | Turbine blade and process for producing this turbine blade |
GB2324835A (en) * | 1994-08-02 | 1998-11-04 | United Technologies Corporation | Method of manufacturing a turbine blade having discharge holes |
US6158961A (en) * | 1998-10-13 | 2000-12-12 | General Electric Compnay | Truncated chamfer turbine blade |
CN1378890A (zh) * | 2001-04-04 | 2002-11-13 | 西门子公司 | 制造涡轮机叶片的方法 |
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GB660282A (en) * | 1948-10-08 | 1951-11-07 | Power Jets Res & Dev Ltd | Improvements in or relating to turbines, compressors and like fluid flow apparatus |
GB916672A (en) * | 1959-12-23 | 1963-01-23 | Prvni Brnenska Strojirna Zd Y | Improvements in and relating to exhaust gas turbines |
GB1158813A (en) * | 1968-03-08 | 1969-07-23 | Rolls Royce | Stator vane for a gas turbine engine |
DE2544612C3 (de) * | 1974-10-14 | 1980-04-10 | Leningradskoe Specialnoe Konstruktorskoe Bjuro Tyaschelych I Unikalnych Stankov, Leningrad (Sowjetunion) | Rundfräsverfahren |
GB2096523B (en) * | 1981-03-25 | 1986-04-09 | Rolls Royce | Method of making a blade aerofoil for a gas turbine |
EP0513223A4 (en) * | 1990-02-06 | 1993-04-07 | General Electric Company | Computer-controlled grinding machine for producing objects with complex shapes |
JPH09502932A (ja) * | 1993-09-29 | 1997-03-25 | シーメンス アクチエンゲゼルシヤフト | 主軸に沿って延びたタービンブレード断面のフライス切削方法 |
US5465780A (en) * | 1993-11-23 | 1995-11-14 | Alliedsignal Inc. | Laser machining of ceramic cores |
US5662160A (en) * | 1995-10-12 | 1997-09-02 | General Electric Co. | Turbine nozzle and related casting method for optimal fillet wall thickness control |
DE10038453A1 (de) * | 2000-08-07 | 2002-02-21 | Alstom Power Nv | Verfahren zur Herstellung eines gekühlten Feingussteils |
DE10064267A1 (de) * | 2000-12-22 | 2002-07-04 | Alstom Switzerland Ltd | Verfahren zum schnellen Herstellen von hohlen Turbinenschaufeln für die Fertigungsentwicklung und Bauteiltests |
DE10064268A1 (de) * | 2000-12-22 | 2002-07-04 | Alstom Switzerland Ltd | Werkzeug und Verfahren zum Giessen eines Formteils für die Herstellung einer Turbinenschaufel |
-
2002
- 2002-11-28 DE DE10255346A patent/DE10255346A1/de not_active Ceased
-
2003
- 2003-11-12 EP EP03104165A patent/EP1424466A3/de not_active Withdrawn
- 2003-11-17 US US10/713,098 patent/US7207108B2/en not_active Expired - Fee Related
- 2003-11-28 CN CNB2003101157863A patent/CN100390377C/zh not_active Expired - Fee Related
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB627295A (en) * | 1946-04-10 | 1949-08-05 | Adrian Albert Lombard | Improvements in or relating to the manufacture of guide vanes for axial-flow turbines and compressors |
US5299353A (en) * | 1991-05-13 | 1994-04-05 | Asea Brown Boveri Ltd. | Turbine blade and process for producing this turbine blade |
GB2324835A (en) * | 1994-08-02 | 1998-11-04 | United Technologies Corporation | Method of manufacturing a turbine blade having discharge holes |
US6158961A (en) * | 1998-10-13 | 2000-12-12 | General Electric Compnay | Truncated chamfer turbine blade |
CN1378890A (zh) * | 2001-04-04 | 2002-11-13 | 西门子公司 | 制造涡轮机叶片的方法 |
Also Published As
Publication number | Publication date |
---|---|
DE10255346A1 (de) | 2004-06-09 |
EP1424466A3 (de) | 2006-08-23 |
US7207108B2 (en) | 2007-04-24 |
US20040111885A1 (en) | 2004-06-17 |
EP1424466A2 (de) | 2004-06-02 |
CN1508394A (zh) | 2004-06-30 |
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