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81. 发明公开

EP1953343A3 Cooling system for a gas turbine blade and corresponding gas turbine blade 无效
标题翻译：冷却系统的燃气涡轮机叶片和enstprechende燃气涡轮叶片
公开(公告)号：EP1953343A3
公开(公告)日：2011-02-02
申请号：EP08250187.5
申请日：2008-01-15
申请人： United Technologies Corporation
发明人： Spangler, Brandon W. , Pietraszkiewicz, Edward F.
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2260/202
摘要： A cooling system for an airfoil portion (112) of a turbine engine component is provided. The cooling system includes a first cavity (142) dedicated to cooling a trailing edge portion (118) of an airfoil portion (112) and a second cavity (146) dedicated to cooling an aft portion (144) of a pressure side wall (114).

82. 发明公开

EP2119873A2 Airfoil with triangular serpentine cooling channels 有权转让
标题翻译： Schaufelblatt mit dreieckigeSerpentinkühlkanälen
公开(公告)号：EP2119873A2
公开(公告)日：2009-11-18
申请号：EP09251011.4
申请日：2009-03-31
申请人： United Technologies Corporation
发明人： Pietraszkiewicz, Edward F. , Pinero, Sandra S.
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2210/44 , F05D2250/185 , F05D2260/202 , Y02T50/676
摘要： A cooled airfoil (32) includes a concave pressure wall (42) extending radially from a base to a tip of the airfoil, a convex suction wall (44) connected to the concave pressure wall at a leading edge (46) and a trailing edge (48) spaced axially from the leading edge, and cooling channels extending radially between the base and the tip of the airfoil between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply through the base of the airfoil. The cooling channels include a leading edge channel (52), a trailing edge channel (54), a serpentine cooling circuit, and a dedicated up-pass channel (58). The serpentine cooling circuit includes a first up-pass channel (56a) forward of the trailing edge channel and configured to be in flow communication with a supply channel through the base of the airfoil, a down-pass channel (56b) forward of and in flow communication with the first up-pass channel, and a second up-pass channel (56c) forward of and in flow communication with the down-pass channel. At least the down-pass channel (56b) and the second up-pass channel (56c) of the serpentine circuit have a generally triangular transverse cross-sectional shape. The dedicated up-pass channel (58) is arranged between the leading edge channel (52) and the second up-pass channel (56c) of the serpentine cooling circuit.
摘要翻译：冷却的翼型件（32）包括从基座向翼型件的尖端径向延伸的凹形压力壁（42），在前缘（46）和后缘（46）处连接到凹形压力壁的凸形抽吸壁（48），其与所述前缘轴向间隔开，并且所述冷却通道在所述基部和所述翼型的所述末端之间径向延伸，所述冷却通道在所述凹压壁和所述凸吸入壁之间，并且构造成接收通过所述翼型件的基部的冷却流体供应。冷却通道包括前缘通道（52），后缘通道（54），蛇形冷却回路和专用上通道（58）。蛇形冷却回路包括后缘通道前方的第一上通道（56a），并被配置为与通过翼型的底座的供应通道流动连通;向下通道（56b）与第一上行通道的流动通信，以及与下行通道向前并与其流动通信的第二上行通道（56c）。至少蛇形回路的下通道（56b）和第二上通道（56c）具有大致三角形的横截面形状。专用上通道（58）布置在蛇形冷却回路的前缘通道（52）和第二上通道（56c）之间。

83. 发明公开

EP2119872A2 Turbine blade internal cooling configuration 有权转让
标题翻译： InterneKühlungskonfigurationfürTurbinenschaufel
公开(公告)号：EP2119872A2
公开(公告)日：2009-11-18
申请号：EP09250885.2
申请日：2009-03-27
申请人： United Technologies Corporation
发明人： Pinero, Sandra S. , Pietraszkiewicz, Edward F. , Dube, Bryan P. , Yee, Stephen J. , Levy, Ryan Shepard , Hassan, Mohamed , Valerio, Domenico , Hartmann, Scott D.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/30 , F05D2260/202 , F05D2260/221 , Y02T50/673 , Y02T50/676
摘要： A cooled airfoil (32) includes a concave pressure wall (42) extending radially from a base to a tip of the airfoil, a convex suction wall (44) connected to the concave pressure wall at a leading edge (46) and a trailing edge (48) spaced axially from the leading edge, and a plurality of cooling channels (56) formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel (52) extending radially from the base toward the tip, a trailing edge channel (54) extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit (56) including a plurality of channels (56a, b, c), and a dedicated up-pass channel (58) extending radially from the base toward the tip between the leading edge channel and the forward most channel (56c) of the plurality of channels in the serpentine cooling circuit.
摘要翻译：冷却的翼型件（32）包括从基座向翼型件的尖端径向延伸的凹形压力壁（42），在前缘（46）和后缘（46）处连接到凹形压力壁的凸形抽吸壁（48），其与前缘轴向间隔开;以及多个冷却通道（56），其形成在所述凹压壁和所述凸吸入壁之间并且构造成从所述翼型件的底部接收冷却流体供应。冷却通道包括从基部朝向顶端径向延伸的前缘通道（52），从底部向顶端径向延伸并与多个后缘孔流动连通的后缘通道（54），其适于排出冷却流体到翼型件的外部，包括多个通道（56a，b，c）的蛇形冷却回路（56）以及从基部朝向前缘的前端延伸的专用上通道（58）通道和蛇形冷却回路中的多个通道的前进通道（56c）。

84. 发明公开

EP1655452A3 Cooling features for an airfoil 有权转让
标题翻译：冷却构造为翼型
公开(公告)号：EP1655452A3
公开(公告)日：2009-09-16
申请号：EP05256849.0
申请日：2005-11-04
申请人： United Technologies Corporation
发明人： Pietraszkiewicz, Edward F. , Coons, Todd , Botnick, Christina
IPC分类号： F01D5/18
CPC分类号： F01D5/147 , F01D5/186 , F01D5/187 , F05D2230/21 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , F28F3/12 , Y10T29/49339 , Y10T29/49341
摘要： A turbine blade airfoil assembly (12) includes a cooling air passage (30). The cooling air passage (30) includes a plurality of impingement openings (32) that are isolated from at least one adjacent impingement opening (32). The cooling air passage (30) is formed and cast within a turbine blade assembly through the use of a single core (44). The single core (44) forms the features required to fabricate the various separate and isolated impingement openings (32). The isolation and combination of impingement openings provides for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.

85. 发明公开

EP1965033A2 Blade outer air seal 有权转让
标题翻译：叶片外部空气密封
公开(公告)号：EP1965033A2
公开(公告)日：2008-09-03
申请号：EP08250692.4
申请日：2008-02-29
申请人： United Technologies Corporation
发明人： Pietraszkiewicz, Edward F. , Peto, Joseph A. , Calderbank, John C. , O'Neill, Lisa P. , Bruskotter, Michael J.
IPC分类号： F01D11/08 , F01D25/24
CPC分类号： F01D11/08 , F01D9/04 , F01D25/246 , F02C7/18 , F05D2230/80 , F05D2230/90 , F05D2240/11 , F05D2260/201 , F05D2260/95 , F05D2300/611
摘要： A turbine engine blade outer air seal segment (20) has a body (22) having a base portion (50). The base portion (50) has a transversely concave ID face (32), a forward end (24), an aft end (26), and first and second circumferential edges (28, 30). The body (22) has at least one mounting hook (42). At least one cover plate (60) is secured to the body (22) to define at least one cavity (92). The cover plate (60) has a plurality of feed holes (64). A plurality of outlet holes (70) extend through the base portion (50) to the ID face (32). At least one of the base portion (50) and cover plate (60) comprises a protruding portion (130) protruding into the cavity (92) to form a partial restriction (124) separating forward and aft cavity portions (120, 122).
摘要翻译：涡轮发动机叶片外部空气密封段（20）具有具有基部（50）的主体（22）。基部（50）具有横向凹入的ID面（32），前端（24），后端（26）以及第一和第二圆周边缘（28,30）。主体（22）具有至少一个安装钩（42）。至少一个盖板（60）固定到主体（22）上以限定至少一个空腔（92）。盖板（60）具有多个供给孔（64）。多个出口孔（70）穿过底座部分（50）延伸到ID面（32）。基部（50）和盖板（60）中的至少一个包括伸入空腔（92）中的突出部分（130）以形成分隔前部和后部空腔部分（120,122）的局部限制部（124）。

86. 发明公开

EP1953343A2 Cooling system for a gas turbine blade and corresponding gas turbine blade 无效
标题翻译： Kühlsystemfüreine Gasturbinenschaufel und enstprechende Gasturbinenschaufel
公开(公告)号：EP1953343A2
公开(公告)日：2008-08-06
申请号：EP08250187.5
申请日：2008-01-15
申请人： United Technologies Corporation
发明人： Spangler, Brandon W. , Pietraszkiewicz, Edward F.
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2260/202
摘要： A cooling system for an airfoil portion (112) of a turbine engine component is provided. The cooling system includes a first cavity (142) dedicated to cooling a trailing edge portion (118) of an airfoil portion (112) and a second cavity (146) dedicated to cooling an aft portion (144) of a pressure side wall (114).
摘要翻译：提供了一种用于涡轮发动机部件的翼型部分（112）的冷却系统。冷却系统包括专用于冷却机翼部分（112）的后缘部分（118）的第一空腔（142）和专用于冷却压力侧壁（114）的后部（144）的第二空腔（146））。

87. 发明公开

EP1944469A2 Turbine blade trip strip orientation 有权转让
标题翻译： Turbinenblatt-Nockenstreifenausrichtung
公开(公告)号：EP1944469A2
公开(公告)日：2008-07-16
申请号：EP07254923.1
申请日：2007-12-18
申请人： United Technologies Corporation
发明人： Pietraszkiewicz, Edward F. , Downs, James P.
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/188 , F05D2240/126 , F05D2240/127 , F05D2250/183 , F05D2250/314 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
摘要： A turbine component (20c) includes a coolant passage (42) and a plurality of trip members (50) that extend within the coolant passage (42). Each of the plurality of trip members (50) includes an orientation relative to an expected flow direction through the coolant passage (42). At least three of the trip members (50) have orientations that are different from each other. For example, the orientations of the trip members (50) may progressively transition along the length of the coolant passage (42).
摘要翻译：涡轮机部件（20c）包括在冷却剂通道（42）内延伸的冷却剂通道（42）和多个跳闸部件（50）。多个跳闸构件（50）中的每一个包括相对于穿过冷却剂通道（42）的预期流动方向的取向。跳闸构件（50）中的至少三个具有彼此不同的取向。例如，跳闸构件（50）的取向可以沿着冷却剂通道（42）的长度逐渐过渡。

88. 发明公开

EP1760265A2 Blade with a cooling microcircuit and corresponding manufacturing method 有权
标题翻译： Bauteil eines Turbinentriebwerks mit einemMikrokühlkreislaufundzugehörigesHerstellungsverfahren
公开(公告)号：EP1760265A2
公开(公告)日：2007-03-07
申请号：EP06254318.6
申请日：2006-08-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Cunha, Frank , Pietraszkiewicz, Edward F. , Sharma, Om Parkash
IPC分类号： F01D5/18 , F01D5/00 , F01D21/00
CPC分类号： B23P15/04 , B22F2998/00 , F01D5/005 , F01D5/187 , F01D5/20 , F01D21/003 , F05D2230/211 , F05D2230/232 , F05D2260/203 , F05D2260/2212 , F05D2260/22141 , Y10T29/49336 , Y10T29/49341 , C22C47/16
摘要： A method for manufacturing a turbine engine component (50) comprises the steps of forming a first half (12) of an airfoil portion (10) of the turbine engine component (50) and forming a plurality of microcircuits (120) having at least one passageway on an exposed internal wall (20) of the first half (12) of the airfoil portion (10). The method further comprises forming a second half (14) of the airfoil portion (10) of said turbine engine component (50), and forming at least one additional cooling microcircuit (120') having at least one passageway on an exposed internal wall (22) of the second half (14) of the airfoil portion (10). Thereafter, the first half (12) is placed in an abutting relationship with the second half (14) after the cooling microcircuits (120,120') have been formed and inspected. The first half (12) and the second half (14) are joined together to form the airfoil portion (10).
摘要翻译：一种用于制造涡轮发动机部件（50）的方法包括以下步骤：形成涡轮发动机部件（50）的翼型部分（10）的第一半部（12），并形成多个微电路（120），该微电路具有至少一个通道在翼型部分（10）的前半部（12）的暴露的内壁（20）上。该方法还包括形成所述涡轮发动机部件（50）的翼型部分（10）的第二半部（14），以及在暴露的内壁上形成至少一个附加的冷却微电路（120'），其具有至少一个通道翼型部分10的后半部分14的端部22）。此后，在冷却微电路（120,120'）已经形成和检查之后，第一半（12）与第二半（14）处于邻接关系。第一半（12）和第二半（14）连接在一起以形成翼型部（10）。

89. 发明公开

EP1760264A2 Turbine engine component and method of making the same 有权
标题翻译：涡轮发动机部件及其制造方法
公开(公告)号：EP1760264A2
公开(公告)日：2007-03-07
申请号：EP06254317.8
申请日：2006-08-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Sharma, Om Parkash , Pietraszkiewicz, Edward F. , Cunha, Frank
IPC分类号： F01D5/18 , F01D5/00
CPC分类号： F01D5/20 , B23P15/04 , F01D5/005 , F01D5/187 , F01D21/003 , F05D2230/211 , F05D2230/232 , F05D2260/203 , F05D2260/2212 , F05D2260/22141 , Y10T29/49336 , Y10T29/49341
摘要： A method for manufacturing a turbine engine component comprises the steps of forming a first half (12) of an airfoil portion (10) of the turbine engine component and forming a first cooling microcircuit (120) having at least one passageway on an exposed internal wall (20) of the first half (12) of the airfoil portion (10). The method further comprises forming a second half (14) of the airfoil portion (10) of said turbine engine component, forming a second cooling microcircuit (120') having at least one passageway on an exposed internal wall (22) of the second half (14) of the airfoil portion (10), and placing the first half (12) in an abutting relationship with the second half (14) after the cooling microcircuits (120,120') have been formed and inspected.
摘要翻译：一种用于制造涡轮发动机部件的方法包括以下步骤：形成涡轮发动机部件的翼型部分（10）的第一半部（12）并在暴露的内壁上形成具有至少一个通道的第一冷却微电路（120）（10）的所述第一半部（12）的所述第一部分（20）。该方法还包括形成所述涡轮发动机部件的翼型部分（10）的第二半部（14），在第二半部的暴露的内壁（22）上形成具有至少一个通道的第二冷却微电路（120'）（14），并且在冷却微电路（120,120'）已经形成和检查之后，将第一半部（12）与第二半部（14）以邻接关系放置。

90. 发明公开

EP1754858A2 Mistake proof identification feature for turbine blades 有权
标题翻译： Verwechslungssicheres IdentifikationsmerkmalfürTurbinenschaufeln
公开(公告)号：EP1754858A2
公开(公告)日：2007-02-21
申请号：EP06254230.3
申请日：2006-08-11
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Kang, Moon-Kyoo Brian , Pietraszkiewicz, Edward F. , Lonczak, Kenneth A.
IPC分类号： F01D5/14 , F01D5/00
CPC分类号： F01D5/18 , F01D5/147 , F05D2230/60 , F05D2250/11 , F05D2250/141 , F05D2250/70 , Y02T50/671 , Y02T50/676
摘要： An identification feature (42) is used to unmistakably identify internal features present in different generations of turbine blade designs. The identification feature (42) is located on a root portion (32) of the turbine blade (20A') and protrudes to provide a visually identifiable feature that is also readable by a coordinate measuring machine, but does not interfere with installation or operation of the turbine blade (20A'). The weight of the identification feature (42) is in a specific proportion to the weight of the turbine blade (20A') in order to prevent interfere with operation of the turbine blade during high-speed rotation in a gas turbine engine.
摘要翻译：识别特征（42）用于明确地识别不同代涡轮叶片设计中存在的内部特征。识别特征（42）位于涡轮叶片（20A'）的根部（32）上并突出以提供可视坐标的特征，该特征也可由坐标测量机读取，但不干扰安装或操作涡轮叶片（20A'）。识别特征（42）的重量与涡轮叶片（20A'）的重量成比例的特定比例，以便在燃气涡轮发动机中高速旋转期间防止涡轮叶片的操作干扰。

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