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公开(公告)号：US07322797B2
公开(公告)日：2008-01-29
申请号：US11296910
申请日：2005-12-08
IPC分类号： F01D5/26
CPC分类号： F01D5/22 , F01D11/006 , F05D2240/81 , F05D2250/292 , F05D2250/314 , Y02T50/671 , Y02T50/676 , Y10S416/50
摘要： A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A damper seat surrounds the portal and is recessed under the platform for receiving a vibration damper to sealingly close the chamber across the portal.
摘要翻译： 涡轮机叶片包括整体连接在一起的翼型件，平台，柄和燕尾榫。 冷却室位于平台下方并具有从柄部向外露出的入口。 阻尼器座圈围绕入口并且凹陷在平台下方，用于接收振动阻尼器以密封地封闭穿过入口的腔室。
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公开(公告)号：US06984103B2
公开(公告)日：2006-01-10
申请号：US10718465
申请日：2003-11-20
IPC分类号： F03D11/00
CPC分类号： F01D5/187 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.
摘要翻译： 涡轮叶片包括具有在前缘和后缘之间延伸的压力和吸力侧壁以及从根部到尖端的翼型件。 燕尾榫在平台上连接到翼型根部。 三个内部冷却回路在翼型内部的跨度上延伸，并且每个回路包括相应的入口通道，其从燕尾榫开始轴向相邻对准。 入口通道从燕尾榫通过平台扭转在一起，并且横跨相邻的侧壁横向相邻对齐，并进入前缘的后翼。
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公开(公告)号：US06382906B1
公开(公告)日：2002-05-07
申请号：US09595867
申请日：2000-06-16
IPC分类号： F01D514
CPC分类号： F01D9/06 , F01D5/18 , F01D5/187 , F01D11/005 , Y02T50/676
摘要： An impingement baffle for a turbine nozzle vane includes a perforate sleeve for discharging impingement air therethrough. A cap closes the sleeve at a top end, and includes an inlet hole. A spoolie cup includes a flange at the bottom thereof which is disposed atop the cap around the inlet hole for channeling air therein. A retainer is joined to the cap to loosely trap the cup flange thereatop for permitting limited lateral sliding movement thereof.
摘要翻译： 用于涡轮喷嘴叶片的冲击挡板包括用于通过其排出冲击空气的穿孔套筒。 盖子在顶端封闭套筒，并包括入口孔。 摆动杯包括在其底部的凸缘，其围绕入口孔设置在帽的顶部，用于在其中引导空气。 保持器连接到盖上，以松动地将杯法兰收集在其上，以允许其有限的横向滑动运动。
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公开(公告)号：US07503749B2
公开(公告)日：2009-03-17
申请号：US11097474
申请日：2005-04-01
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/13 , F05D2250/184 , F05D2250/292 , F05D2260/221 , Y02T50/673 , Y02T50/676
摘要： An airfoil for a gas turbine engine has opposed pressure and suction sidewalls extending between a leading edge and a trailing edge. The airfoil includes an array of radially-spaced apart longitudinally-extending lands which define a plurality of trailing edge slots therebetween. Each of the trailing edge slots has an inlet in fluid communication with an interior of the airfoil and an exit in fluid communication with the trailing edge. At least one of the lands is tapered such that a width of the land measured in a radial direction decreases from the suction sidewall to the pressure sidewall.
摘要翻译： 用于燃气涡轮发动机的翼型件具有在前缘和后缘之间延伸的相对的压力和吸力侧壁。 翼型件包括在其间限定多个后缘槽的径向间隔开的纵向延伸的平台的阵列。 每个后缘槽具有与翼型件的内部流体连通的入口和与后缘流体连通的出口。 至少一个焊盘是锥形的，使得沿径向测量的焊盘的宽度从抽吸侧壁减小到压力侧壁。
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公开(公告)号：US07387492B2
公开(公告)日：2008-06-17
申请号：US11312059
申请日：2005-12-20
IPC分类号： F01D25/12
CPC分类号： F01D5/186 , F05D2240/122 , F05D2240/304 , Y02T50/676
摘要： A method facilitates fabricating an airfoil for use with a turbine blade. The method comprises forming a substantially solid ceramic airfoil core, inserting the core into a die and casting the airfoil with a pressure side wall and a suction side wall connected together at a leading edge and a trailing edge, such that a plurality of first trailing edge slots and at least one second trailing edge slot extend from the trailing edge along the pressure side wall, wherein the second trailing edge slot has a length, measured between an inlet and an exit of the slot, that is longer than a corresponding length of each of the plurality of first trailing edge slots.
摘要翻译： 一种方法有助于制造与涡轮叶片一起使用的翼型件。 该方法包括形成基本上固体的陶瓷翼型芯，将芯插入模具中并且在前缘和后缘连接有压力侧壁和吸力侧壁的情况下铸造翼型件，使得多个第一后缘 槽和至少一个第二后缘槽沿着所述压力侧壁从所述后缘延伸，其中所述第二后缘槽具有在所述槽的入口和出口之间测量的长度，所述长度大于每个的相应长度 的多个第一后缘槽。
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公开(公告)号：US07296973B2
公开(公告)日：2007-11-20
申请号：US11294063
申请日：2005-12-05
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality of independent cooling circuits are disposed inside the airfoil correspondingly along the pressure and suction sidewalls thereof. A first serpentine circuit is disposed along the pressure sidewall. A second serpentine circuit is disposed along the suction sidewall in parallel with the first circuit. And a third impingement circuit is disposed at the leading edge forward of the first and second circuits.
摘要翻译： 涡轮机叶片包括具有相对的压力和抽吸侧壁的翼型件，其在相对的前缘和后缘处连接在一起并且从根部到尖端纵向延伸。 多个独立的冷却回路相应地沿其压力和吸力侧壁设置在翼型内。 第一蛇形电路沿着压力侧壁设置。 第二蛇形电路沿着吸力侧壁与第一回路并联设置。 并且第三冲击电路设置在第一和第二电路的前方的前缘。
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公开(公告)号：US07140835B2
公开(公告)日：2006-11-28
申请号：US10956299
申请日：2004-10-01
IPC分类号： F01D9/02
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.
摘要翻译： 涡轮喷嘴包括连接到相对的内部和外部带的中空叶片。 内带包括在叶片的前缘下方的前唇，在叶片的后缘下方的后唇，以及间隔开的安装凸缘。 冲击孔从安装凸缘的底部在内带的角部向后缘倾斜地向后延伸，用于冲击冷却。
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公开(公告)号：US06672829B1
公开(公告)日：2004-01-06
申请号：US10196623
申请日：2002-07-16
申请人： David Glenn Cherry , Ching-Pang Lee , Chander Prakash , Aspi Rustom Wadia , Brian David Keith , Steven Robert Brassfield
发明人： David Glenn Cherry , Ching-Pang Lee , Chander Prakash , Aspi Rustom Wadia , Brian David Keith , Steven Robert Brassfield
IPC分类号： F01D518
CPC分类号： F01D5/141 , F01D5/145 , F01D5/20 , F05D2250/292
摘要： A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.
摘要翻译： 一种用于燃气涡轮发动机的涡轮机叶片，包括翼型件和整体式燕尾榫，用于将翼型件沿着径向轴线安装到涡轮机外罩内侧的转子盘。 所述翼型件还包括：在前缘和后缘处连接在一起的第一和第二侧壁，其中所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到顶板，用于在其上引导燃烧气体; 以及在前缘和后缘之间从顶板向外延伸的至少一个尖端肋。 尖端肋被定向成使得纵向延伸通过的轴线相对于径向轴线成一定角度，用于涡轮叶片的至少一个轴向长度的指定部分。 这种角度在指定部分可以是基本相同的，或者可以在其上变化。 因此，燃烧气体的再循环区域形成在尖端肋的远端附近，这减少了涡轮叶片至少轴向长度的指定部分的翼型和护罩之间的燃烧气体的泄漏流。
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公开(公告)号：US20080145234A1
公开(公告)日：2008-06-19
申请号：US11641286
申请日：2006-12-19
CPC分类号： B22C9/103 , F01D5/187 , F05D2230/211 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A casting core for a turbine blade includes a plurality of rods extending above a shank. The rods define internal cooling channels in the airfoil of the blade, and the shank defines an inlet channel in the dovetail of the blade. A plurality of stubs are clustered together at a bulb joined to the shank and radiate outwardly to integrally join different ones of the rods for increasing strength of the core.
摘要翻译： 用于涡轮叶片的铸芯包括在柄上方延伸的多个杆。 杆在叶片的翼型中限定内部冷却通道，并且杆在叶片的燕尾形中限定入口通道。 多个短棒在连接到柄的灯泡上聚集在一起并向外辐射以一体地连接不同的杆，以增加芯的强度。
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公开(公告)号：US07293961B2
公开(公告)日：2007-11-13
申请号：US11294218
申请日：2005-12-05
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/185 , F05D2260/201 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil includes pressure and suction sidewalls spaced apart to define flow channels extending in span and separated by ribs. Side channels are disposed along one sidewall and spaced from the opposite sidewall by the ribs, and a mid channel bridges the sidewalls. The side and mid channels are arranged in a zigzag serpentine cooling circuit alternating therebetween for transferring heat from the sidewall into the mid channel.
摘要翻译： 涡轮机翼片包括间隔开的压力和抽吸侧壁，以限定在跨度中延伸并由肋分隔的流动通道。 侧通道沿着一个侧壁设置并且通过肋与相对侧壁间隔开，并且中间通道桥接侧壁。 侧通道和中间通道以锯齿形蛇形冷却回路布置，用于将热量从侧壁传送到中间通道。
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