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1. 发明公开

EP3428397A1 BLADE AND CORRESPONDING METHOD OF COOLING A TIP RAIL 审中-公开
公开(公告)号：EP3428397A1
公开(公告)日：2019-01-16
申请号：EP18182280.0
申请日：2018-07-06
申请人： General Electric Company
发明人： DYSON, Thomas Earl , RATHAY, Nicholas William , LEARY, Brendon James , GARAY, Gregory Terrence , LEDEZMA, Gustavo Adolfo , WEBER, David Wayne , SMITH, Aaron Ezekiel
IPC分类号： F01D5/20
摘要： An apparatus and method for cooling a blade tip 90 for a turbine engine 10 can include a blade 68, such as a cooled turbine blade, having a tip rail 96, 196, 296, 396 extending beyond a tip wall 94 enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

2. 发明公开

EP3184742A1 TURBINE AIRFOIL WITH TRAILING EDGE COOLING CIRCUIT 有权转让
标题翻译：涡轮机翼带后缘边冷却回路
公开(公告)号：EP3184742A1
公开(公告)日：2017-06-28
申请号：EP16203705.5
申请日：2016-12-13
申请人： General Electric Company
发明人： SMITH, Aaron Ezekiel , FOSTER, Gregory Thomas , IDUATE, Michelle Jessica , LEARY, Brendon James , WEBER, David Wayne
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/304 , F05D2260/201 , F05D2260/203 , F05D2260/22141 , Y02T50/676
摘要： One aspect of the disclosure provides for a turbine airfoil (122). The turbine airfoil (122) may include a trailing edge (158) having: a set of cooling channels (210, 310), having a first cooling channel (212, 312) fluidly connected to a second cooling channel (216, 316); a first section (220, 320) having a first pin bank cooling arrangement (224, 324), the first section (220, 320) fluidly connected to the first cooling channel (212, 312); a second section (230, 330) having a second pin bank cooling arrangement (232, 332), the second section (230, 330) fluidly connected to the second cooling channel (216, 316) and being radially inward of the first section (220, 320); and a pressure side panel (240, 340) having a third pin bank cooling arrangement (244, 344), the pressure side panel fluidly connected to the first cooling channel (212, 312).
摘要翻译：本公开的一个方面提供了一种涡轮机翼型（122）。涡轮翼型件（122）可以包括后缘（158），其具有：一组冷却通道（210,310），其具有流体连接到第二冷却通道（216,316）的第一冷却通道（212,312）; 具有第一销排冷却装置（224,324）的第一部分（220,320），所述第一部分（220,320）流体连接到所述第一冷却通道（212,312）; 具有第二销排冷却装置（232,332）的第二部分（230,330），所述第二部分（230,330）流体地连接到所述第二冷却通道（216,316）并且在所述第一部分的径向内部（ 220，320）; 和具有第三销排冷却装置（244,344）的压力侧面板（240,340），所述压力侧面板流体连接到所述第一冷却通道（212,312）。

3. 发明授权

EP3184737B1 MULTI-WALL BLADE WITH COOLING CIRCUIT 有权转让
公开(公告)号：EP3184737B1
公开(公告)日：2019-02-20
申请号：EP16202423.6
申请日：2016-12-06
申请人： General Electric Company
发明人： SMITH, Aaron Ezekiel , FOSTER, Gregory Thomas , WEBER, David Wayne , WEBER, Jospeh Anthony
IPC分类号： F01D5/18

4. 发明授权

EP3184739B1 MULTI-WALL BLADE WITH COOLING CIRCUIT 有权转让
公开(公告)号：EP3184739B1
公开(公告)日：2018-10-03
申请号：EP16203125.6
申请日：2016-12-09
申请人： General Electric Company
发明人： SMITH, Aaron Ezekiel , FOSTER, Gregory Thomas
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , Y02T50/676
摘要： A cooling system according to an embodiment includes: a leading edge cooling circuit (30) including a pressure side (8) serpentine circuit and a suction side (10) serpentine circuit; a first mid-blade cooling circuit including a suction side (10) serpentine circuit; a second mid-blade cooling circuit including a pressure side (8) serpentine circuit; a trailing edge (16) cooling circuit; and at least one air feed for supplying cooling air (32, 34, 36, 50, 52, 60, 132, 232, 332) to the leading edge (14, 16) cooling circuit, the first mid-blade cooling circuit, the second mid-blade cooling circuit, and the trailing edge (16) cooling circuit.

5. 发明公开

EP3184737A1 COOLING CIRCUIT FOR A MULTI-WALL BLADE 有权转让
标题翻译：用于多壁刀片的冷却回路
公开(公告)号：EP3184737A1
公开(公告)日：2017-06-28
申请号：EP16202423.6
申请日：2016-12-06
申请人： General Electric Company
发明人： SMITH, Aaron Ezekiel , FOSTER, Gregory Thomas , WEBER, David Wayne , WEBER, Jospeh Anthony
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F02C3/04 , F05D2220/32 , F05D2240/305 , F05D2240/307 , F05D2250/185 , F05D2260/202
摘要： A cooling system according to an embodiment includes: a three-pass serpentine cooling circuit (40, 140, 240); and an air feed cavity (41, 141, 241) for supplying cooling air to the three-pass serpentine cooling circuit (40, 140, 240); wherein the three-pass serpentine cooling circuit (40, 140, 240) extends radially outward from and at least partially covers at least one central plenum (20) and a first set of near wall cooling channels (18) of a multi-wall blade (6).
摘要翻译：根据一个实施例的冷却系统包括：三路蛇形冷却回路（40,140,240）; 和用于向三通蛇形冷却回路（40,140,240）供应冷却空气的供气腔（41,141,241）; 其中所述三通蛇形冷却回路（40,140,240）从至少一个中央增压室（20）和多壁叶片的第一组近壁冷却通道（18）径向向外延伸并且至少部分地覆盖所述至少一个中央增压室（20）（6）。

6. 发明公开

EP3156594A1 TURBINE BLADE 审中-公开
标题翻译： TURBINENSCHAUFEL
公开(公告)号：EP3156594A1
公开(公告)日：2017-04-19
申请号：EP16191837.0
申请日：2016-09-30
申请人： General Electric Company
发明人： KRUMANAKER, Matthew Lee , BERGHOLZ, Robert Frederick , SMITH, Aaron Ezekiel , DOOLEY, Weston Nolan
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/187 , F05D2260/203 , F05D2260/941 , Y02T50/676
摘要： An engine 10 comprises an airfoil 78 having at least one internal cooling circuit extending radially from the longitudinal axis 12 of the engine 10. The cooling circuit is defined by at least one rib 122 extending across an interior 96 of the airfoil 78 and at least one internal wall 126 defining an internal passage 120. The internal wall 126 further defines one or more near wall cooling passages 132. A thermal stress reduction structure 140 is provided between the rib 122 and the internal wall 126, providing efficient cooling at a junction 136 between the rib 122 and the internal wall 126.
摘要翻译：发动机10包括具有从发动机10的纵向轴线12径向延伸的至少一个内部冷却回路的翼型件78.冷却回路由延伸穿过翼型件78的内部96的至少一个肋122限定，并且至少一个内壁126限定内部通道120.内壁126进一步限定一个或多个近壁冷却通道132.热应力减小结构140设置在肋122和内壁126之间，从而在第122 肋122和内壁126。

7. 发明公开

EP3428398A1 AIRFOIL AND CORRESPONDING METHOD OF COOLING A TIP RAIL 审中-公开
公开(公告)号：EP3428398A1
公开(公告)日：2019-01-16
申请号：EP18182282.6
申请日：2018-07-06
申请人： General Electric Company
发明人： RATHAY, Nicholas William , DYSON, Thomas Earl , LEARY, Brendon James , GARAY, Gregory Terrence , LEDEZMA, Gustavo Adolfo , WEBER, David Wayne , SMITH, Aaron Ezekiel
IPC分类号： F01D5/20
摘要： An apparatus and method for cooling an airfoil tip 90 for a turbine engine 10 can include a blade 68, such as a cooled turbine blade, having a tip rail 96, 196, 296, 396 extending beyond a tip wall 94 enclosing an interior for the airfoil at the tip. A plurality of film-holes 112, 212, 312, 412 can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the airfoil to cool the tip of the airfoil.

8. 发明公开

EP3184744A1 COOLING CIRCUITS FOR A MULTI-WALL BLADE 审中-公开
标题翻译：用于多壁刀片的冷却电路
公开(公告)号：EP3184744A1
公开(公告)日：2017-06-28
申请号：EP16205155.1
申请日：2016-12-19
申请人： General Electric Company
发明人： SMITH, Aaron Ezekiel , WEBER, David Wayne
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/188 , F05D2220/30 , F05D2240/305 , F05D2240/306 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A cooling system for a multi-wall blade (6) according to an embodiment includes: a primary cooling air feed (34) for providing cooling air (32); and a feed splitter (80) coupled to the primary cooling air feed (34) for splitting the cooling air (32) provided by the primary cooling air feed (34) between a pressure side (8) cooling circuit and a suction side (10) cooling circuit.
摘要翻译：根据一个实施例的用于多壁叶片（6）的冷却系统包括：用于提供冷却空气（32）的主冷却空气进给（34）; （8）冷却回路和吸入侧（10）之间分开由主冷却空气供给（34）提供的冷却空气（32）的供给分流器（80））冷却回路。

9. 发明公开

EP3184743A1 TURBINE AIRFOIL WITH TRAILING EDGE COOLING CIRCUIT 有权转让
标题翻译：涡轮机翼带后缘边冷却回路
公开(公告)号：EP3184743A1
公开(公告)日：2017-06-28
申请号：EP16204828.4
申请日：2016-12-16
申请人： General Electric Company
发明人： WEBER, David Wayne , FOSTER, Gregory Thomas , IDUATE, Michelle Jessica , LEARY, Brendon James , SMITH, Aaron Ezekiel
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/041 , F05D2220/32 , F05D2240/304 , F05D2260/20 , F05D2260/2212 , Y02T50/676
摘要： One aspect of the disclosure provides for a turbine airfoil 122. The turbine airfoil 122 may include a trailing edge 158 having: a set of cooling channels 210, 310 having a first cooling channel 212 fluidly connected to a second cooling channel 216, 316; a first section 220, 320 having a first pin bank cooling arrangement 224, 324, the first section 220, 320 fluidly connected to the first cooling channel 212, 312; and a second section 230, 330 having a second pin bank cooling arrangement 232, 332, the second section 230, 330 fluidly connected to the second cooling channel 216, 316 and being radially inward of the first section 220, 320.
摘要翻译：本公开的一个方面提供了涡轮机翼122.涡轮机翼122可包括后缘158，其具有：一组冷却通道210,310，其具有流体连接到第二冷却通道216,316的第一冷却通道212; 具有第一销排冷却装置224,324的第一部分220,320，第一部分220,320流体连接到第一冷却通道212,312; 以及具有第二销排冷却装置232,332的第二部分230,330，第二部分230,330流体连接到第二冷却通道216,316并且在第一部分220,320的径向内部。

10. 发明公开

EP3184739A1 COOLING CIRCUITS FOR A MULTI-WALL BLADE 有权转让
标题翻译：用于多壁刀片的冷却电路
公开(公告)号：EP3184739A1
公开(公告)日：2017-06-28
申请号：EP16203125.6
申请日：2016-12-09
申请人： General Electric Company
发明人： SMITH, Aaron Ezekiel , FOSTER, Gregory Thomas
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , Y02T50/676
摘要： A cooling system according to an embodiment includes: a leading edge cooling circuit (30) including a pressure side (8) serpentine circuit and a suction side (10) serpentine circuit; a first mid-blade cooling circuit including a suction side (10) serpentine circuit; a second mid-blade cooling circuit including a pressure side (8) serpentine circuit; a trailing edge (16) cooling circuit; and at least one air feed for supplying cooling air (32, 34, 36, 50, 52, 60, 132, 232, 332) to the leading edge (14, 16) cooling circuit, the first mid-blade cooling circuit, the second mid-blade cooling circuit, and the trailing edge (16) cooling circuit.
摘要翻译：根据一个实施例的冷却系统包括：前缘冷却回路（30），其包括压力侧（8）蛇形回路和吸入侧（10）蛇形回路; 第一中叶片冷却回路，其包括吸入侧（10）蛇形回路; 包括压力侧（8）蛇形回路的第二中间叶片冷却回路; 后缘（16）冷却回路; 以及至少一个空气供给装置，用于将冷却空气（32,34,36,50,52,60,132,232,332）供给至所述前缘（14,16）的冷却回路，所述第一中叶片冷却回路，所述第二中叶片冷却回路第二中叶片冷却回路和后缘（16）冷却回路。

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