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1. 发明授权

EP3112599B1 TRANSFER TUBE AND TURBINE SECTION COMPRISING TRANSFER TUBE 有权转让
公开(公告)号：EP3112599B1
公开(公告)日：2020-11-25
申请号：EP16167690.3
申请日：2016-04-29
申请人： United Technologies Corporation
发明人： WAITE, Ryan Alan , JACQUES, Jeffrey Michael , HAGAN, Benjamin F.
IPC分类号： F01D9/06 , F01D25/12

2. 发明授权

EP3091183B1 THERMAL REGULATION CHANNELS FOR TURBOMACHINE COMPONENTS 有权转让
公开(公告)号：EP3091183B1
公开(公告)日：2020-11-11
申请号：EP16159166.4
申请日：2016-03-08
申请人： United Technologies Corporation
发明人： WAITE, Ryan Alan , HAGAN, Benjamin F.
IPC分类号： F01D5/18

3. 发明公开

EP3067520A1 GAS POWERED TURBINE COMPONENT INCLUDING SERPENTINE COOLING 审中-实审转让
标题翻译： GASBETRIEBENE TURBINENKOMPONENTE MIT SERPENTINENKÜHLUNG
公开(公告)号：EP3067520A1
公开(公告)日：2016-09-14
申请号：EP16158547.6
申请日：2016-03-03
申请人： United Technologies Corporation
发明人： WAITE, Ryan Alan , HAGAN, Benjamin F.
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/185 , F01D5/186 , F01D5/187 , F01D9/065 , F01D25/12 , F05D2250/185 , Y02T50/676
摘要： A flow path component (200) for a gas powered turbine including a flow path component body having cross sectional profile having a leading edge (230) and a trailing edge (240), the leading edge (230) being connected to the trailing edge (240) by a first side (210) and being connected to the trailing edge (240) by a second side (220) opposite the first side (210), a serpentine cooling passage including a plurality of segments (202,204,206), each of the segments (202,204,206) being generally radially aligned, wherein a first subset (202,204) of the segments disposed along one of the first side (210) and the second side (220) of the cross sectional profile, and a second subset (206) of the segments spans the flow path component body from the first side (210) to the second side (220), and a cavity (250) internal to the flow path component body, wherein the cavity (250) is at least partially shielded from one of the first side (210) and the second side (220) by at least one of the plurality of segments (202,204,206).
摘要翻译：一种用于燃气动力涡轮机的流路部件（200），其包括具有前缘（230）和后缘（240）的横截面轮廓的流路部件主体，所述前缘（230）连接到所述后缘 240），并且通过与第一侧（210）相对的第二侧（220）连接到后缘（240），蛇形冷却通道包括多个段（202,204,206），每个段段（202,204,206）通常径向对齐，其中沿着横截面轮廓的第一侧（210）和第二侧（220）中的一个设置的段的第一子集（202,204）和第二子集所述段从所述第一侧（210）到所述第二侧（220）跨过所述流路部件主体，以及在所述流路部件主体内部的空腔（250），其中所述腔（250）至少部分地与所述腔的第一侧（210）和第二侧（220）中的至少一个的段（202,204,206）。

4. 发明公开

EP2993301A1 SHIELDED PASS THROUGH PASSAGE IN A GAS TURBINE ENGINE STRUCTURE 有权转让
标题翻译：爱尔兰GASTURBINENMOTORSTRUKTUR的阿富汗德黑兰
公开(公告)号：EP2993301A1
公开(公告)日：2016-03-09
申请号：EP15182775.5
申请日：2015-08-27
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , WAITE, Ryan Alan
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F02C7/18 , F01D5/147 , F01D5/187 , F01D9/04 , F02C3/04 , F05D2220/32 , F05D2260/202 , Y02T50/676
摘要： A gas turbine engine structure includes a body (100) radially spanning an inner portion (120) and an outer portion (110). The body (100) includes a first passage (150,160) interior to the structure body (100). The first passage (150,160) includes a first opening on one of a radially outward edge and a radially inward edge of the structure, and a second opening on the other of the radially outward edge and the radially inward edge of the structure. A second passage (170) is also included interior to the structure, approximately aligned with the first passage (150,160), and disposed between the first passage (150,160) and one of a first surface (190) and a second surface (180) of the structure. The second passage (170) insulates the first passage (150,160) from heat transfer through one of the first second surfaces.
摘要翻译：燃气涡轮发动机结构包括径向跨越内部部分（120）和外部部分（110）的主体（100）。主体（100）包括在结构体（100）内部的第一通道（150,160）。第一通道（150,160）包括在结构的径向向外边缘和径向向内边缘中的一个上的第一开口，以及在结构的径向向外边缘和径向向内边缘中的另一个的第二开口。第二通道（170）还包括在结构内部，大致与第一通道（150,160）对齐，并且设置在第一通道（150,160）与第一通道（150,160）和第一表面（190）和第二表面（180）结构。第二通道（170）将第一通道（150,160）与热传递隔离通过第一第二表面之一。

5. 发明公开

EP2885507A2 THREADED FULL RING INNER AIR-SEAL 有权转让
标题翻译：全螺纹环车内空气密封
公开(公告)号：EP2885507A2
公开(公告)日：2015-06-24
申请号：EP13845065.5
申请日：2013-07-23
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , CAPRARIO, Joseph T.
IPC分类号： F01D11/08 , F01D5/20 , F02C7/28
CPC分类号： F01D11/001 , F01D9/065 , F01D11/02 , F05D2240/11
摘要： A disclosed vane assembly includes a vane section formed of a plurality of circumferentially spaced fixed vanes. The vanes extend radially outward from an inner platform and hooked into case. The inner platform includes a mount rail extending radially inwardly from the inner platform. An air seal is attached to the inner platform of the vane section and includes a ring extending circumferentially about the axis. The disclosed air seal includes a plurality of tabs that receive lugs disposed on the mount rail. A ring nut is secured to the air seal and engaged to the mount rail for securing the vane section to the air seal.

6. 发明授权

EP2885507B1 THREADED FULL RING INNER AIR-SEAL 有权转让
标题翻译：螺纹全环内部空气密封
公开(公告)号：EP2885507B1
公开(公告)日：2018-04-18
申请号：EP13845065.5
申请日：2013-07-23
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , CAPRARIO, Joseph T.
IPC分类号： F01D11/08 , F01D5/20 , F02C7/28 , F01D11/02
CPC分类号： F01D11/001 , F01D9/065 , F01D11/02 , F05D2240/11
摘要： A disclosed vane assembly includes a vane section formed of a plurality of circumferentially spaced fixed vanes. The vanes extend radially outward from an inner platform and hooked into case. The inner platform includes a mount rail extending radially inwardly from the inner platform. An air seal is attached to the inner platform of the vane section and includes a ring extending circumferentially about the axis. The disclosed air seal includes a plurality of tabs that receive lugs disposed on the mount rail. A ring nut is secured to the air seal and engaged to the mount rail for securing the vane section to the air seal.

7. 发明公开

EP3219930A1 BLADE OUTER AIR SEAL WITH A HEAT SHIELD 有权转让
标题翻译：刀片外部空气密封与热屏蔽
公开(公告)号：EP3219930A1
公开(公告)日：2017-09-20
申请号：EP17161109.8
申请日：2017-03-15
申请人： United Technologies Corporation
发明人： McCAFFREY, Michael G. , HAGAN, Benjamin F. , GRIFFIN, David Richard , BALAWAJDER, Peter , CORCORAN, Christopher
IPC分类号： F01D9/04 , F01D25/24 , F01D11/08
CPC分类号： F01D11/08 , F01D5/02 , F01D9/04 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2260/231 , F05D2300/10 , Y02T50/672 , Y02T50/675
摘要： A seal assembly (60) includes a seal arc segment (66) that defines radially inner and outer sides (R1, R2) with the radially outer side (R2) including radially-extending sidewalls (74). A radially inner surface (76) joins the radially-extending sidewalls (74). The radially-extending sidewalls (74) and the radially inner surface (76) define a pocket (78). A rail shield (80) has radially-extending walls (82) lines the radially-extending sidewalls (74).
摘要翻译：密封组件（60）包括密封弧段（66），所述密封弧段（66）限定径向内侧和外侧（R1，R2），径向外侧（R2）包括径向延伸侧壁（74）。径向内表面（76）连接径向延伸的侧壁（74）。径向延伸的侧壁（74）和径向内表面（76）限定了凹穴（78）。导轨护罩（80）具有沿径向延伸的侧壁（74）的径向延伸壁（82）。

8. 发明公开

EP3054094A1 GAS TURBINE ENGINE TURBINE VANE BAFFLE AND SERPENTINE COOLING PASSAGE 有权转让
标题翻译：燃气涡轮发动机涡轮叶片挡板和蛇形冷却通道
公开(公告)号：EP3054094A1
公开(公告)日：2016-08-10
申请号：EP16154523.1
申请日：2016-02-05
申请人： United Technologies Corporation
发明人： SPANGLER, Brandon W. , WAITE, Ryan Alan , GAUTSCHI, Steven Bruce , HAGAN, Benjamin F.
IPC分类号： F01D5/18
CPC分类号： F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
摘要： An airfoil (78) for a gas turbine engine includes pressure and suction side walls (90, 92) joined to one another at leading and trailing edges (82, 84). The pressure and suction side walls (90, 92) surround an airfoil cavity (96) and provide an exterior airfoil surface (94). A baffle (98) is arranged in the airfoil cavity (96) and includes a supply hole (120). Ribs (100-108) extend from the pressure and suction side walls (90, 92) into the airfoil cavity (96) and engage the baffle (98). The ribs (100-108) are configured to provide a serpentine cooling passage (112) between the baffle (98) and at least one of the pressure and suction side walls (90, 92). The serpentine cooling passage (112) has first and second passes (116, 118) joined by a bend (117). The ribs (100-108) form a film cooling cavity (110) between the first and second passes (116, 118). The supply hole (120) fluidly connects the baffle (98) to the film cooling cavity (110). Film cooling holes (122) extend through at least one of the pressure and suction side walls (90, 92). The film cooling holes (122) are in fluid communication with the film cooling cavity (110).
摘要翻译：用于燃气涡轮发动机的翼型件（78）包括在前缘和后缘（82,84）处彼此连接的压力侧壁和吸力侧壁（90,92）。压力和吸入侧壁（90,92）围绕翼型腔（96）并且提供外部翼型表面（94）。挡板（98）布置在翼型腔（96）中并且包括供应孔（120）。肋（100-108）从压力和吸入侧壁（90,92）延伸到翼型腔（96）中并与挡板（98）接合。肋（100-108）构造成在挡板（98）与压力侧壁和吸力侧壁（90,92）中的至少一个之间提供蛇形冷却通道（112）。蛇形冷却通道（112）具有由弯头（117）连接的第一和第二通道（116,118）。肋（100-108）在第一和第二通道（116,118）之间形成薄膜冷却腔（110）。供应孔（120）将挡板（98）流体连接到膜冷却腔（110）。薄膜冷却孔（122）延伸穿过压力侧壁和吸入侧壁（90,92）中的至少一个。膜冷却孔（122）与膜冷却腔（110）流体连通。

9. 发明公开

EP3051065A1 CORED AIRFOIL PLATFORM WITH OUTLET SLOTS 有权转让
标题翻译：麻省理工大学麻省理工学院麻省理工学院麻省理工学院
公开(公告)号：EP3051065A1
公开(公告)日：2016-08-03
申请号：EP16152007.7
申请日：2016-01-20
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , WAITE, Ryan Alan , DUBE, Bryan P. , MONGILLO Jr., Dominic J.
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/187 , F01D5/147 , F01D5/18 , F01D5/225 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F05D2260/22141
摘要： An airfoil (20) includes a platform (22) that has platform leading and trailing ends (28,30), lateral side faces (32,34), and inner and outer faces (36,38). An airfoil portion (24) extends outwardly from the inner face (36) of the platform (22). The airfoil portion (24) includes airfoil leading and trailing ends (40,42) and side walls (44,46) that join the airfoil leading and trailing ends (40,42). The platform (22) includes a cooling passage (50) that has an inlet (54) at a forward location, outlet slots (56) at the platform trailing end (30), and an intermediate passage portion (58) that extends from the inlet (54) to the outlet slots (56). The intermediate passage portion (58) includes a common manifold region (60) that feeds the outlet slots (56).
摘要翻译：机翼（20）包括具有平台前端和后端（28,30），横向侧面（32,34）以及内表面（36,38）的平台（22）。机翼部分（24）从平台（22）的内表面（36）向外延伸。机翼部分（24）包括连接翼型件前端和后端（40,42）的翼型件前端和后端（40,42）和侧壁（44,46）。平台（22）包括在前部位置具有入口（54）的冷却通道（50），平台尾端（30）处的出口狭槽（56）和从中间通道部分（58）延伸的中间通道部分入口（54）到出口槽（56）。中间通道部分（58）包括供给出口槽（56）的公共歧管区域（60）。

10. 发明授权

EP3060760B1 AIRFOIL WITH SKIN CORE COOLING 有权转让
公开(公告)号：EP3060760B1
公开(公告)日：2018-12-05
申请号：EP14855974.3
申请日：2014-10-16
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , WAITE, Ryan Alan
IPC分类号： F01D5/18 , F01D25/12 , F02C7/18
CPC分类号： F01D25/12 , F01D5/187 , F01D9/041 , F01D9/065 , F04D29/542 , F04D29/5846 , F05D2220/32 , F05D2240/81 , F05D2260/202 , F05D2260/204 , Y02T50/676
摘要： A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.

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